US Pat. No. 9,287,983

OPTICAL DATA TRANSMISSION SYSTEM

Airbus Defence and Space ...

1. An optical data transmission system comprising:
a device;
a first optical maintenance port;
a second optical maintenance port;
an optical signal splitter coupled to each of the first optical maintenance port and second optical maintenance port; and
a solid-state bound data line, coupled to the device and the optical signal splitter, the solid-state bound data line configured
to transmit data using electromagnetic energy between the device and the first optical maintenance port and the second optical
maintenance port, wherein the solid-state bound data line is interrupted by a gap between (i) the device and (ii) the optical
signal splitter, wherein the gap is configured to transmit electromagnetic signals between the device and the optical signal
splitter, and to reflect electromagnetic signals emanating from the first optical maintenance port to the second optical maintenance
port, by way of the optical signal splitter, thereby further enabling data transmission between the first optical maintenance
port and the second optical maintenance port.

US Pat. No. 9,327,823

DEVICE FOR REDUCING STRUCTURAL VIBRATIONS OF AIRFOILS

Airbus Defence and Space ...

1. A device to reduce structural vibrations of airfoils in an aircraft, the device comprising:
at least one force generator arranged in winglets provided on ends of the airfoils, the at least one force generator acting
substantially in a direction of movement of the vibrations;

wherein fluid from fuel tanks arranged in an area of airfoil tips is moveable in an oscillatory manner as a vibrating mass
of the at least one force generator.

US Pat. No. 9,571,802

METHOD FOR THE DETECTION OF PULSED LASER RADIATION AND IMAGING LASER ALERTER

Airbus Defence and Space ...

1. A method for detecting pulsed laser radiation having two-dimensional resolution of the direction of incidence with a CCD
sensor having an imaging optic, comprising:
generating, in a signal processing having a sampling frequency of at least 5 kHz, single images by comparing each pixel of
the CCD sensor to a respective threshold value and by storing a pixel value that exceeds the respective threshold value for
an image processing;

ascertaining, in the signal processing, a mean value or peak value of the stored pixel values of the single image pixel-by-pixel
over at least 10 samples;

forwarding a signal image obtained in the signal processing for image processing at an image frequency of 10 Hz to 500 Hz;
identifying from the signal image, in an image processing, at least one signal pixel representing incident laser radiation;
and

determining a direction of the incidence of the laser radiation from a position of the signal pixels on the signal image.

US Pat. No. 9,569,668

METHOD AND DEVICE FOR IMAGE-ASSISTED RUNWAY LOCALIZATION

Airbus Defence and Space ...

1. A method of localizing a runway based on feature analysis of an image including the runway, the method comprising:
rotating the image to a horizontally-oriented image according to an angle of rotation;
generating a feature image comprising image features of the horizontally-oriented image and a mirrored feature image of the
feature image comprising mirrored image features of the horizontally-oriented image;

generating a feature matching image having a plurality of lines, each line of the plurality of lines in the feature matching
image indicating a line maximum according to a correlation between image features and mirrored image features in individual
corresponding lines of the feature image and the mirrored feature image, the line maximum for each line in the feature matching
image given as:

V(k)=IFFT(FFT(M1(k))*CONJ(FFT(M2(k))) ), with

FFT: fast Fourier transform;
IFFT: inverse fast Fourier transform;
M1: the feature image;

M2: the mirrored feature image;

M1(k): k-th line of the feature image;

M2(k): k-th line of the mirrored feature image; and

CONJ: complex conjugation.

US Pat. No. 9,360,092

PNEUMATICALLY ACTUATED DECOUPLING DEVICE

Airbus Defence and Space ...

1. A pneumatic decoupling device for an electromechanical actuator element, the pneumatic decoupling device comprising:
a pressure accumulator element with an outlet; and
a tripping mechanism, configured to release pressure stored in the pressure accumulator element in a controlled manner,
wherein the outlet of the pressure accumulator element is configured so that it is coupleable to the electromechanical actuator
element, and

wherein the pneumatic decoupling device is configured so that tripping the tripping mechanism releases the pressure stored
in the pressure accumulator element to the electromechanical actuator element to trigger a decoupling function in the electromechanical
actuator element.

US Pat. No. 9,864,715

BUS SYSTEM USING PLURALITY OF NON-OVERLAPPING FREQUENCY BANDS FOR COMMUNICATION

Airbus Defence and Space ...

1. A bus system associated with a network partitioned into multiple virtual connections, the bus system comprising:
a bus having two signal lines with analog signals applied on the bus within non-overlapping frequency bands;
a plurality of data processing units, each of the data processing units assigned with a distinct non-overlapping mid-frequency
band, the bus connecting the data processing units to the network using direct point-to-point or point-to-multipoint virtual
connections based at least on one distinct non-overlapping mid-frequency band; and

a modem unit coupling each data processing unit with the bus using the two signal lines of the bus, the modem unit comprising:
an interface unit connectable with each data processing unit to communicate using the direct point-to-point or point-to-multipoint
virtual connections with each data processing unit using a digital communication protocol;

a modulation unit that converts flow of data into a signal that is transferable using the non-overlapping frequency bands;
a filter bank synthesis unit comprising a polyphase filter bank that converts the data of the interface unit on the distinct
mid-frequency band assigned to the data processing unit and suppresses interferences between adjacent non-overlapping frequency
bands;

a D/A converter that converts the signal of the filter bank synthesis unit into an analog signal;
a bus-coupling unit configured to inductively or capacitively couple the analog signal of the D/A converter that is transmitted
onto the bus in a galvanically isolated manner, and to inductively or capacitively decouple one or more analog signals received
from the bus in a galvanically isolated manner;

an A/D converter that digitizes the analog signals received from the bus-coupling unit;
a filter bank analysis unit comprising a polyphase filter bank that partitions the digitized signals into the distinct non-overlapping
frequency bands, and feeds data to the interface unit based on its assigned non-overlapping frequency band; and

a demodulation unit that demodulates the data of the filter bank analysis unit, and feeds user data to the interface unit,
wherein the bus system transmits data using the direct point-to-point or point-to-multipoint virtual connections while minimizing
interference between the multiple virtual connections, wherein only every second frequency band of the non-overlapping frequency
bands is utilized exclusively.

US Pat. No. 9,595,172

DATAGLOVE HAVING TACTILE FEEDBACK AND METHOD

Airbus Defence and Space ...

1. A data glove for generating tactile feedback at a user's finger upon touching the finger to an interaction element on an
infrared touchscreen, wherein the data glove comprises:
receiving elements configured to receive fingers of an operator;
stimulators configured to generate tactile feedback and attached to the finger-receiving elements;
a plurality of infrared photodetectors configured to identify a finger touching the infrared touchscreen; and
a signal generator configured to excite a stimulator of the finger touching the infrared touchscreen upon successful actuation
of the interaction element on the infrared touchscreen,

wherein the plurality of infrared photodetectors is arranged at the data glove and each of the plurality of infrared photodetectors
is assigned to one of the receiving elements,

wherein each of the plurality of infrared photodetectors is configured to detect infrared rays emitted by the infrared touchscreen
based on a distance of the respective one of the plurality of infrared photodetectors from the infrared touchscreen, and

wherein the finger for which a corresponding one of the plurality of infrared photodetectors provides a maximum photocurrent
is identified as the finger touching the infrared touchscreen.

US Pat. No. 9,283,414

SOLID PROPELLANT GAS GENERATOR, EXTINGUISHING DEVICE, METHOD FOR COOLING A FLOWING MIXTURE AND METHOD FOR EXTINGUISHING A FIRE

Airbus Defence and Space ...

1. A solid propellant gas generator, comprising:
a housing containing a solid propellant, which is separated from a surrounding area, that is released as a flowing mixture
into the surrounding area; and

a cooling system configured to cool the flowing mixture, wherein the cooling system has at least one feed device configured
to feed a gas from the surrounding area to the flowing mixture so that gas from the surrounding area mixes with the flowing
mixture prior to entering into the surrounding area,

wherein the cooling system comprises:
an acceleration device configured to accelerate the flowing mixture,
an introducing device configured to introduce the flowing mixture into the surrounding area, and
a linear contact region of acceleration device and introducing device, wherein the feed device is arranged at the linear
contact region.

US Pat. No. 9,129,719

IONS METERING DEVICE FOR AN ENERGY STORAGE DEVICE, METHOD OF MANUFACTURING A METERING DEVICE AND ION ENERGY STORAGE DEVICE

Airbus Defence and Space ...

1. An ion dosage apparatus for an energy storage apparatus, comprising:
a first energy guiding device having a first energy supply device configured to supply a first energy to the first energy
guiding device; and

a separation device,
wherein in a first state in which no energy is supplied via the first energy supply device, the separation device is configured
to block ions from being transported past the first energy guiding device;

wherein the first energy guiding device is configured to specify a transport direction of the first energy to guide the first
energy to a preset position of the separation device and to emit the first energy to the separation device at the preset position,

wherein in a second state in which the first energy is supplied via the first energy supply device, the separation device
is configured to control a volume of emitted first energy, a number of ions transported by the separation device past the
first energy guiding device, or a number of ions permitted to pass by the separation device.

US Pat. No. 9,747,453

TESTING INTEGRATED INDEPENDENT LEVELS OF SECURITY COMPONENTS HOSTED ON A VIRTUALIZATION PLATFORM

AIRBUS OPERATIONS SAS, T...

1. A virtualization platform comprising:
a plurality of integrated independent levels of security components, interconnected via communication channels,
integrated interceptor modules connected to said security components via said communication channels, wherein each integrated
interceptor module being interposed in the communication channel connecting two components, wherein each integrated interceptor
module is implemented by multiple threads comprising a first testing thread adapted to transmit data from an integrated analyzing
device to a receiver component, and a second testing thread adapted to transmit data from a sender component into said analyzing
device; and

the integrated analyzing device connected to said integrated interceptor modules and comprising a control device and a testing
device,

said control device being configured to put each interceptor module in an operational mode selected out of a set of predetermined
operational modes including a testing mode, and

said testing device being configured to locally test the components connected to the interceptor modules being put in the
testing mode, wherein in a testing mode a first testing thread of a first integrated interceptor module connected to a component
under test is adapted to perform a blocked read on a destination port connected to the testing device and to introduce testing
packets from the testing device into the component under test, and in that a second testing thread of a second integrated
interceptor module connected to the component under test is adapted to transmit an output result from the component under
test into the testing device, and perform a blocked read on the destination of a queuing channel connected to the sender component,
said testing device being configured to test the reaction of the component under test by analyzing said output result;

wherein the integrated interceptor module, the integrated analyzing device, control device, testing device, the first testing
thread, the second testing thread, the sender component, and the receiver component are implemented using one or more hardware
processing unit.

US Pat. No. 9,404,796

OPTICAL SENSOR ARRANGEMENT

Airbus Defence and Space ...

1. An optical sensor arrangement, comprising:
an aperture; and
first and second sensors configured to detect electromagnetic waves passing through the aperture, wherein the first and second
sensors are physically arranged in series so that electromagnetic waves passing through the aperture pass through the first
sensor and then to the second sensor,

wherein the first and second sensors have a same operational spectral region and cover a same region of surroundings to be
observed,

wherein the first sensor forms an attenuation filter for the second sensor, which is arranged downstream from the first sensor
in a direction of the electromagnetic waves passing through the aperture, and

wherein the first sensor comprises a first diode and the second sensor comprises a second diode, and wherein the first diode
is thicker than the second diode such that a majority of intensity entering the aperture is absorbed by the first sensor,
wherein the intensity absorbed by the first diode is on the order of 99%.

US Pat. No. 9,361,543

AUTOMATIC LEARNING METHOD FOR THE AUTOMATIC LEARNING OF FORMS OF APPEARANCE OF OBJECTS IN IMAGES

Airbus Defence and Space ...

1. An automatic learning method for automatic learning of forms of appearance of objects in images in a form of object features
from training images for using learned object features in an image processing system, the method comprising:
providing training images and associated annotation images, wherein a training image contains a representation of an object
to be learned, and an associated annotation image has positive annotations at positions of objects in the training image and
negative annotations at positions in the training image where no object to be learned is represented;

producing a feature image from the training image, wherein a feature at an image position in the feature image is extracted
from surroundings of a corresponding image position in the training image;

generating a classification image from the feature image and object features, the classification image containing image positions
at which classification responses are contained, the classification responses providing information on a degree of similarity
between the object features and the feature image;

determining a feature contribution of the training image to the object features by weighted summation of training image features
contained in the feature image using a linear spatial filtering operation based on information at least from the annotation
image, the feature image, and the classification image.

US Pat. No. 9,193,469

AIRCRAFT ENGINE WITH AN APPARATUS FOR PULSATING EXPIRATION OF GAS INTO THE EXHAUST NOZZLE

AIRBUS DEFENCE AND SPACE ...

1. An aircraft jet engine, comprising:
an exhaust-gas nozzle having a device configured to blow out an exhaust gas in a pulsating manner into an exhaust-gas stream
so as to reduce noise, the exhaust-gas nozzle including two rows of openings arranged axially one behind the other and configured
to blow the exhaust gas in and out alternatingly, the two rows of openings being distributed along a circumference of the
exhaust-gas nozzle and disposed upstream from a nozzle outlet so as to generate a pulsed turbulence layer around the circumference
of the exhaust-gas nozzle, the openings communicating with the device;

wherein the device comprises an annular space that surrounds a nozzle channel and that is divided by a partition wall into
two annular chambers, each of the two annular chambers communicating with a respective one of the two rows of the openings,
the partition wall being configured to move in an oscillating manner so as to alternatingly increase a size of one of the
annular chambers and correspondingly decrease a size of the other one of the annular chambers.

US Pat. No. 9,080,450

STIRLING ENGINE WITH FLAPPING WING FOR AN EMISSION-FREE AIRCRAFT

Airbus Defence and Space ...

1. An aircraft with an emission-free drive, comprising:
a drive device, comprising a flapping wing device, structured and arranged to generate thrust;
a lift device structured and arranged to generate lift; and
a heat engine, comprising at least one flat-plate Stirling engine drivable by solar thermal radiation, structured and arranged
to convert thermal energy into kinetic energy to drive the drive device,

the flapping wing device including at least one flapping wing, which is pivotable transverse to a flight direction,
wherein a working chamber is arranged between a wing top and a wing underside, and a displacer is arranged to divide the working
chamber into a first and a second chamber region and, with movement, to displace a working gas from one of the first and second
chamber region into the other of the first and second chamber region; and

wherein the top of the wing forms a first side of the flat-plate Stirling engine with a first temperature and the underside
of the wing forms a second side of the flat-plate Stirling engine with a second temperature, in which the second temperature
is lower than the first temperature.

US Pat. No. 9,612,922

COMPUTER SYSTEM AND METHOD FOR COMPARING OUTPUT SIGNALS

Airbus Defence and Space ...

1. A computer system, comprising:
at least three commercial off-the-shelf (COTS) processor cores; and
an evaluation device, which is connected to the at least three COTS processor cores, the evaluation device is configured to
evaluate output signals that are output from the at least three COTS processor cores, wherein the evaluation device includes
a comparator configured to compare a relocatable group of the output signals that are output with one another in pairs, wherein
the comparator of the evaluation device is also configured to output a comparison signal that corresponds to the respective
comparison of the relocatable group of the output signals, and wherein

at least one of the COTS processor cores is different than the other COTS processor cores,
a selection device, connected to the comparator of the evaluation device, configured to select an output signal for further
processing based on the comparison signal,

the at least three COTS processor cores each comprise a corresponding comparator to compare non-relocatable output signals
of the output signals with one another, and

the computer system further comprises a switching device that is connected between the COTS processor cores and the comparator
of the evaluation device, wherein the switching device is configured to transmit the relocatable group of the output signals
to the comparator of the evaluation device on the basis of a utilization state of the comparator of the evaluation device.

US Pat. No. 9,387,930

STEALTH AERIAL VEHICLE

Airbus Defence and Space ...

1. An aerial vehicle, comprising:
at least one turbine configured to propel the aerial vehicle, the at least one turbine including at least one turbine opening;
and

at least one landing gear bay configured to accommodate a landing gear of the aerial vehicle inside the aerial vehicle,
wherein the aerial vehicle has a low radar signature,
wherein the at least one turbine opening and the at least one landing gear bay are disposed on a first side of the aerial
vehicle,

wherein a second side of the aerial vehicle has a smaller radar signature than the first side, and
wherein the second side has no bays.

US Pat. No. 9,162,770

ELECTRIC DRIVE DEVICE FOR AN AIRCRAFT

Airbus Defence and Space ...

1. A drive device for an aircraft, comprising at least a battery for storage of electrical energy, an electric motor for the
propulsion of a propeller, a conductive means for transferring the electrical energy from the battery to the electric motor,
and a first control means for controlling the electric motor, wherein
the battery is a lithium-air battery, the electric motor is a high-temperature superconductor motor, that at least one reservoir
for a coolant and a cooling system connected with the reservoir for cooling the high-temperature superconductor motor is provided,
wherein the cooling system comprises a second control means for controlling the cooling system,

a first means for the variable configuration of the lithium-air battery and/or a second means for the variable configuration
of the reservoir in the aircraft is/are provided, and

a third control means for controlling the first and/or the second means is provided, wherein the control of the first and/or
the second means occurs such that the lithium air-battery and/or the reservoir in the aircraft are configured such that a
mass increase of the lithium-air battery which results during an operation of the drive device and a mass decrease of the
liquid nitrogen in the reservoir that results during an operation of the drive device will not change a center of gravity
position of the aircraft.

US Pat. No. 9,113,248

DIAPHRAGM ARRANGEMENT FOR GENERATING SOUND

Airbus Defence and Space ...

1. A diaphragm arrangement configured to be fitted to a structural component for the purpose of generating sound, the diaphragm
arrangement comprising:
an electrically conductive diaphragm which can oscillate,
two piezo crystals which are fitted opposite one another on either side of the electrically conductive diaphragm,
wherein the piezo crystals are each fastened to the diaphragm,
wherein the piezo crystals are each electrically conductively connected to a separate contact plate on their side opposite
said diaphragm, a pair of contact strips extending substantially in the direction of the structural component, wherein the
first contact strip includes a free end and a second opposite end connected to one of the contact plates, and wherein the
second contact strip includes a free end and a second opposite end connected to the other of the two contact plates, wherein
each free end has an electrical connection contact point.

US Pat. No. 9,476,967

METHOD OF KINEMATIC RANGING

Airbus Defence and Space ...

1. A method of kinematic ranging comprising the steps of:
(i) measuring a bearing al in azimuth of a jammer at a time t1 with respect to a first position using an airborne radar detector located at a first position;

(ii) measuring a rate of change d?/dt of the bearing in azimuth of the jammer with respect to the first position using the
airborne radar detector located at the first position;

(iii) causing the airborne radar detector to carry out a manoeuvre such that it is displaced to a second position by a horizontal
displacement d having orthogonal components ?x, ?y in a time ?t=t2?t1 and measuring a bearing ?2 in azimuth of the jammer at time t2 with respect to the second position using the airborne radar detector located at the second position, where d=?{square root over (?x2+?y2)};

(iv) calculating a difference ?? in the bearing in azimuth of the jammer between the second and first positions;
wherein components ?x, ?y are calculated by the steps of
(a) choosing a desired relative range accuracy ?R/R for the method;

(b) obtaining an estimated range Rest of the jammer from the second position at time t2;

(c) finding d based on the relative range accuracy, the estimated range Rest, the variance ???2 in ?? and the variance ?d2 in d according to


(d) calculating the components ?x, ?y of the displacement d according to
?x=cos(?1+?·?t)·d
?y=?sin(?1+?·?t)·d
wherein a range R of the jammer from the second position is calculated according to

US Pat. No. 9,392,650

DEVICE AND METHOD FOR GENERATING LIGHT OF A PREDETERMINED SPECTRUM WITH AT LEAST FOUR DIFFERENTLY COLORED LIGHT SOURCES

Airbus Defence and Space ...

1. A lighting device comprising:
a lighting unit comprising at least four light sources, each light source having a different color spectra;
a color rendering index calculation unit to calculate a color rendering index based on stored data on spectra of the light
sources and individual first drive data for the light sources;

a drive unit to individually energize the light sources of the lighting unit according to the individual first drive data;
a sensor to measure a spectral power distribution emitted by the lighting unit;
a control unit configured to:
receive the spectral power distribution, a predetermined spectral power distribution, and the color rendering index associated
with weighted sensor values calculable from the individual first drive data;

maximize the color rendering index according to a condition that an error between the predetermined spectral power distribution
and the measured spectral power distribution is smaller than a limit value;

determine individual second drive data based on the color rendering index as maximized; and
act on the drive unit such that the light sources of the lighting unit are individually energized according to the individual
second drive data.

US Pat. No. 9,708,074

AUXILIARY DRIVE SYSTEM FOR A HELICOPTER

Airbus Defence and Space ...

1. A helicopter with a drive system, comprising:
a main drive configured to drive a lift-generating rotor of the helicopter;
a flywheel mass battery comprising at least one flywheel;
a first transmission coupling the flywheel mass battery to the main drive such that, during operation of the main drive, output
is transferred from the main drive to the flywheel mass battery;

a second, variable transmission connecting the flywheel mass battery to the lift-generating rotor of the helicopter such that
a predetermined output is transferred to the lift-generating rotor through adjustment of a transmission ratio of the variable
transmission; and

a main transmission between the main drive and the lift-generating rotor,
wherein the main transmission comprises a first input with which the main drive is coupled,
wherein the main transmission has a second input with which the flywheel mass battery is coupled via the variable transmission.

US Pat. No. 9,568,305

METHOD AND SYSTEM FOR MEASURING THE THICKNESS OF ICE ON A SURFACE, NOTABLY OF AN AIRCRAFT, USING A LUMINOUS PATTERN GENERATED BY DIFFUSION IN THE ICE

AIRBUS OPERATIONS (S.A.S....

1. A system for measuring a thickness of ice on a surface of an aircraft, the system comprising:
a light source configured to project a collimated beam onto the surface to generate a luminous pattern by diffusion in the
ice;

an imaging device configured to acquire an image of the ice including the luminous pattern;
a measuring unit configured to measure on the image a luminous intensity profile of the luminous pattern, wherein the luminous
intensity profile comprises a curve representing intensity of the luminous pattern as a function of a distance from a point
of penetration of the collimated beam into the ice, and wherein the light source is oriented with respect to the surface so
that the luminous intensity profile has a summit at the point of penetration; and

a calculation unit configured to estimate the thickness of ice present on the surface as a function of the luminous intensity
profile,

wherein the measuring unit is configured to measure a width of the summit of the intensity profile and the calculation unit
is configured to estimate the thickness of ice as a function of the width of the summit of the intensity profile and from
at least one predetermined table.

US Pat. No. 9,365,286

REVERSIBLE DECOUPLING DEVICE FOR ACTUATORS

Airbus Defence and Space ...

1. A reversible decoupling device for an actuator element having a drive unit, which includes first and second actuator drive
elements configured to functionally interact to change a length of the actuator element, the reversible decoupling device
comprising:
decoupling mechanism, which comprises
a decoupling drive element;
a first force element;
a second force element;
a first form-fit element; and
a second form-fit element;
wherein the first force element is configured to hold the first form-fit element in a closed position;
wherein the decoupling drive element is configured to move the first form-fit element from the closed position to a form-fit
released position;

wherein the second force element is configured to move the second form-fit element from a closed position to a form-fit released
position;

wherein the second force element is blocked by a positive fit of the first form-fit element such that the second form-fit
element cannot be moved to the form-fit released position; and

wherein the second force element is configured to move the second form-fit element to the form-fit released position in which
a positive fit of the first form-fit element is released;

wherein the decoupling mechanism is configured to decouple an output piston from one of the first and second actuator drive
elements so that the change in length of the actuator element is achievable independently of the drive unit and without decoupling
the first drive element and the second drive element.

US Pat. No. 9,746,563

WIRELESS LOCAL MESSAGING SYSTEM AND METHOD OF DETERMINING A POSITION OF A NAVIGATION RECEIVER WITHIN A WIRELESS LOCAL MESSAGING SYSTEM

Airbus Defence and Space ...

1. A wireless local messaging system, comprising:
at least one transmitter; and
at least one receiver, wherein the at least one transmitter is configured to transmit a local message and a local PRN code
to the at least one receiver;

wherein said at least one receiver is a navigation receiver configured to receive and process navigation messages from satellites
of a global navigation satellite system on a particular carrier frequency, each of the satellites transmitting the navigation
messages with a satellite-individual PRN code,

wherein the at least one transmitter is configured to transmit the local message and the local PRN code in a local message
signal on the particular carrier frequency,

wherein the at least one receiver is further configured to receive and process the local message signal in order to determine
the local PRN code and the local message,

wherein the local PRN code is not used by a satellite of said global navigation satellite system, and
wherein the local message comprises information for a non-global-navigation-satellite-system service.

US Pat. No. 9,308,691

DEVICE AND METHOD FOR PRODUCING A THREE DIMENSIONAL OBJECT

Airbus Defence and Space ...

1. A device for producing a three dimensional object from a powdery material by solidifying layer by layer the powdery material
through the application of energy, the device comprising:
a working surface;
an application device configured to apply predefined, locally different amounts of powdery material of the powdery material
onto the working surface; and

a solidifying device configured to solidify the powdery material applied onto the working surface,
wherein the application device comprises
a transfer device, which can be magnetized and/or can be electrostatically charged and discharged and which is configured
to transfer the powdery material to the working surface; and

a magnetizing or charging device configured to magnetize or electrostatically charge and discharge the transfer device.

US Pat. No. 9,432,135

INTERFACE DEVICE AND METHOD FOR EXCHANGING USER DATA

Airbus Defence and Space ...

1. An interface apparatus for exchange of different time-critical user data between a host device and a divided medium, comprising:
a first interface for exchange of the different time-critical user data with the host device;
a second interface for exchange of the different time-critical user data with the divided medium;
a resource management device;
a temporary memory device;
wherein the first interface works with a first clock pulse;
wherein the second interface works with a second clock pulse, which differs from the first clock pulse;
wherein the first interface and the second interface are connected with the temporary memory device, in order to allow exchange
of the different time-critical user data between the first interface and the second interface, by way of the temporary memory
device;

wherein the resource management device is configured to control the exchange of the different time-critical user data between
the first interface and the second interface, in such a manner that collisions of the different time-critical user data within
the interface apparatus and/or on the divided medium are avoided, in order to allow deterministic behavior during the exchange
of the different time-critical user data; and

wherein the resource management device is further configured to control the temporary memory device in such a manner that
the different time-critical user data is temporarily storable, using the temporary memory device, in such a manner that a
clock pulse difference between the first clock pulse and the second clock pulse is balanced out,

wherein a transmission frame of a collision recognition protocol is generated in the interface apparatus, in which collision
recognition protocol the functionality of a layer has been enriched by a command/response protocol.

US Pat. No. 9,397,408

ANTENNA ARRAY

AIRBUS DEFENCE AND SPACE ...

1. A phased array antenna comprising:
a plurality of antenna elements;
an antenna baseplate on which the plurality of antenna elements are arranged in a regular grid;
a dielectric wide angle impedance match (WAIM) layer structured and arranged in front of the antenna elements to match impedance
for skew angles between 0° and 60°;

wherein the WAIM layer comprises a monolithic material layer from which spacers are machined in a regular grid that corresponds
to the grid of the antenna elements, and wherein the spacers are arranged between the antenna elements.

US Pat. No. 9,239,029

NOZZLE ARRANGEMENT FOR A GAS TURBINE ENGINE

Airbus Defence and Space ...

1. A nozzle arrangement for a gas turbine engine, said nozzle arrangement comprising:
an engine nozzle;
an ejector nozzle arranged to receive a downstream gas flow that exits the engine nozzle;
a gap formed between an outlet of the engine nozzle and an inlet of the ejector nozzle; and
a flange which reduces the gap, and is arranged at a downstream extremity of the engine nozzle, around a periphery of an opening
of said outlet of the engine nozzle, and extends radially outward therefrom, wherein the flange is arranged in an inlet region
of the ejector nozzle.

US Pat. No. 9,837,859

WIRELESS REMOTE ENERGY SUPPLY FOR UNMANNED AERIAL VEHICLES

Airbus Defence and Space ...

1. A transmitter unit for wireless transmission of power by way of a bundled laser beam, comprising:
a laser fiber bundle having a plurality of laser fibers, wherein each laser fiber is designed to emit a laser beam;
a positioning optics for adjusting an emission direction of the bundled laser beam;
a field lens; and
a primary lens,
wherein the plurality of laser fibers is configured to each emit a laser beam, which passes through the positioning optics,
the field lens and the primary lens such that the laser beam emitted by the transmitter unit is emitted in bundled form,

wherein the transmitter unit is configured such that each laser beam passes through the positioning optics, then the field
lens and then the primary lens, in that order.

US Pat. No. 9,796,476

SEAT ASSEMBLY, SEAT ARRANGEMENT AND PASSENGER CABIN FOR AN AIRCRAFT

AIRBUS DEFENCE AND SPACE ...

1. A seat assembly for forming at least one seat of a seat arrangement for a passenger cabin of an aircraft, the seat assembly
comprising:
at least one seat structure, which has
a seat backrest forming a backrest surface,
a seat cushion element for forming a seat surface, and
a passenger space partition, which is arranged to spatially partition a passenger space of the seat and which at least partially
surrounds the seat structure and leaves open an access to the seat structure,

wherein the seat cushion element is moveable between
a comfort position in which the seat cushion element projects further into the access to provide a larger seat surface, and
an access position in which the seat cushion element does not project as far or does not project at all into the access to
provide a wider access,

wherein the seat cushion element is configured to be moveable relative to the seat backrest in such a way that in the access
position at least a portion of the seat surface extends horizontally under and beyond the backrest so that the seat surface
has a variable depth between the access and comfort positions,

wherein the seat cushion element is moveable, when seen or projected in the horizontal direction, between the comfort position
and the access position by 7 cm to 26 cm to provide a seat surface that is 7 cm to 26 cm lower in the comfort position than
in the access position.

US Pat. No. 9,397,765

METHOD FOR THE SELF-TESTING OF A REACTIVE RADIO INTERFERER

Airbus Defence and Space ...

1. A method for the self-testing of a reactive radio interferer comprising a plurality of time-synchronized transmission/reception
paths, the method comprising:
alternately running each of the plurality of time-synchronized transmission/reception paths through an observation phase for
reception of radio spectrum and an interference phase for the transmission of an interference signal based on the radio spectrum
received in the observation phase;

transmitting, by a first one of the time-synchronized transmission/reception paths, a plurality of test signals within said
alternately running observation phases;

receiving, by a second one of the plurality of time-synchronized transmission/reception paths, the plurality of transmitted
test signals; and

analyzing, by the second one of the plurality of time-synchronized transmission/reception paths, the plurality of received
test signals.

US Pat. No. 9,387,937

EJECTION DEVICE FOR A FLIGHT DATA RECORDER

Airbus Defence and Space ...

1. An ejection device for a flight data recorder, the ejection device comprising:
an ejection spindle comprising an ejection rod, the ejection rod movably received within a central cavity of the ejection
spindle, the ejection rod having a recess in an outer surface thereof and a movable locking element engaging the outer surface
and movable between a locking position and an unlocking position, wherein in the unlocking position the movable locking element
is received within the recess;

a bayonet connection, wherein the ejection spindle is configured to be releasably connected to the flight data recorder via
the bayonet connection through engagement of the bayonet connection with the movable locking element when the movable locking
element is in the locking position, wherein the bayonet connection is configured to be released upon movement of the ejection
rod such that the movable locking element moves into the recess of the ejection rod and thereby disengages from the bayonet
fastening;

a disengagement device having a gas pressure generator and a pressure-resistant housing, wherein the ejection spindle is screwable
into the disengagement device; and

a moveable valve arranged inside the disengagement device, the valve being configured to assume a first operating position
when the ejection spindle is screwed into the disengagement device and to assume a second operating position when the ejection
spindle is not screwed into the disengagement device, wherein the moveable valve is spring biased towards the second operating
position,

wherein the first operating position permits a flow connection between an outlet of the gas pressure generator and the ejection
spindle, and

wherein the second operating position prevents the flow connection between the outlet of the gas pressure generator and the
ejection spindle;

wherein, when the valve is in the first operating position, the ejection rod of the ejection spindle is movable by gas pressure
upon actuation of the gas pressure generator to move the locking element from the locked position and the unlocked position.

US Pat. No. 9,303,588

SOUND ABSORBER, SOUND ABSORBER ASSEMBLY AND AN ENGINE WITH A SOUND ABSORBER ASSEMBLY

Airbus Defence and Space ...

1. A sound absorber for an engine of an aircraft, the sound absorber comprising:
a base body having a bottom plate, a wall enclosing the bottom plate and an opening enabling entry of air into the base body;
and

a tongue having a fixed end connected to the wall, a free end and a central portion disposed between the fixed end and the
free end;

the tongue further having a longitudinal direction extending from the fixed end towards the free end, a width direction extending
substantially perpendicularly to the longitudinal direction, and a transverse direction extending substantially perpendicularly
to the longitudinal direction and substantially perpendicularly to the width direction,

the central portion having a first free edge extending in the longitudinal direction from the fixed end towards the free end,
and a second free edge opposite to the first free edge and extending in the longitudinal direction from the fixed end towards
the free end,

the tongue dividing a space of the base body into a partial space adjacent to the bottom plate and a partial space adjacent
to the opening, the two partial spaces being connected to each other via a gap,

the free end being disposed at a first distance from the wall in the transverse direction and at a second distance from the
bottom plate in the longitudinal direction, such that the first and the second distances determine a size of the gap, and

the central portion being configured to extend at least partially straight along the width direction.

US Pat. No. 9,851,485

HOLLOW OPTICAL WAVEGUIDE WITH OPENINGS, PARTICULARLY FOR SUPPLYING A PHOTOBIOREACTOR WITH LIGHT AND NUTRIENTS

Airbus Defence and Space ...

1. A photobioreactor comprising:
a container for accommodating organisms in a solution;
at least one optical waveguide having a transparent material and being configured to guide light, the at least one optical
waveguide extending into the container and configured to supply the organisms in the container with light, wherein a hollow
core is formed by the transparent material to supply the organisms in the container with nutrients, wherein the nutrients
transferred in the hollow core exit the at least one optical waveguide outwards and into the solution surrounding the at least
one optical waveguide in the container;

a light source, coupled to the at least one of the optical waveguides in such a manner that light from the light source is
coupled into the transparent material of the optical waveguide and can be transferred via the optical waveguide into a solution,
to which solution organisms have been added, and

a nutrient source, which is connected to at least one of the optical waveguides in such a manner that nutrients from the nutrient
source are introduced into the hollow core of the optical waveguide and can be transferred via the same into the solution,
to which solution organisms have been added.

US Pat. No. 9,573,682

SYSTEM FOR A VEHICLE WITH REDUNDANT COMPUTERS

Airbus Defence and Space ...

1. A control and/or management system for a vehicle, the system comprising:
maneuvering actuators configured to maneuver the vehicle;
system actors configured to control inner system components of the vehicle;
sensors configured to acquire data associated with the system actors or maneuvering actuators; and
at least two redundant computers configured to control or manage the vehicle,
wherein the system further comprises at least one of
at least two redundant vehicle management computers communicatively interconnected with the maneuvering actuators, system
actors, and sensors, wherein one of the at least two redundant vehicle management computers is configured to generate system
control commands for each maneuvering actuators and for each system actor based on the data acquired by the sensors,

wherein one of the at least two redundant vehicle management computers is configured to receive control commands or sensor
data from at least one other vehicle management computer and is configured to compare control commands or sensor data from
different vehicle management computers to determine errors of a vehicle management computer,

wherein a first one of the at least two redundant vehicle management computer is directly connected to a first sensor and
a second of the at least two redundant vehicle management computer is directly connected to a second sensor,

wherein data received from the first sensor in the first vehicle management computer is transmitted by the first vehicle management
computer to the second vehicle management computer,

wherein, in the case both vehicle management computers are operating correctly, the first vehicle management computer is configured
to process the data from the first sensor and/or to generate control commands for an actuator associated with the first sensor,
and the second vehicle management computer is configured to process the data from the second sensor and/or to generate control
commands for an actuator associated with the second sensor,

wherein the first vehicle management computer is configured to transmit data received from the first sensor in the first vehicle
management computer to the second vehicle management computer, and

wherein, when fault control commands generated by the first vehicle management computer are detected, the second vehicle management
computer is configured to take over the role of the first vehicle management computer and to generate the control commands
for the first actuator.

US Pat. No. 9,796,133

WELDING TOOL COMPRISING A ROTATING PROBE, WELDING METHOD AND WORKPIECE

Airbus Defence and Space ...

1. A welding tool for joining at least two workpieces at a joining region by friction stir welding, the welding tool comprising:
a tool pin arranged along one axis of the welding tool, wherein the tool pin is configured to apply frictional heat to the
workpieces at the joining region during the friction stir welding; and

shoulder surrounding the tool pin, wherein the shoulder is arranged to separate the joining region from a surrounding area,
wherein the shoulder is configured to be moveable parallel to the one axis,

wherein the tool pin has, in a direction of the one axis, a projection that projects beyond the shoulder end region,
wherein the projection is controlled by a displacement of the shoulder parallel to the one axis.

US Pat. No. 9,530,330

DEVICE FOR VISUALIZING MILITARY OPERATIONS

Airbus Defence and Space ...

1. A device for visualizing military operations for depicting a scenario for a plurality of action subjects, each of the plurality
of action subjects being respectively controlled by a representative, wherein the device for visualizing military operations
comprises:
a first memory unit configured to store the scenario;
a first representation unit configured to represent the stored scenario; and
a computing unit configured to control the first representation unit in such a way that the stored scenario, including a plurality
of moveable and fixed scenario objects, together with the action subjects controlled by the plurality of representatives are
reproduced on the first representation unit, wherein the reproduction on the first representation unit occurs over time with
the moveable scenario objects and the action subjects moving over the time of the reproduction and movement of the moveable
scenario objects being controlled by the device,

wherein the first representation unit is a shared representation unit for the plurality of representatives such that all representatives
being part of the visualized military operation are able to view the scenario depicted on the first representation unit;

a plurality of input units,
wherein each of the plurality of input units is configured to transmit control signals to the computing unit,
wherein the computing unit is configured to control an action subject in the scenario, associated with an input unit, corresponding
to the control signals of the associated input, and

wherein each of the plurality of input units is configured to control at least one moveable object displayed on the shared
representation unit;

a second memory unit configured to store a plurality of state vectors, wherein each of the plurality of state vectors contains
properties of the moveable scenario objects at a particular time during the reproduction;

a configuration unit configured to receive an instruction to replay the reproduction at a specified time and an assignment
of one of the plurality of moveable objects to one of the plurality of representatives, wherein in response to receipt of
the instruction

the computing unit retrieves a first state vector of the plurality of state vectors corresponding to the specified period
of time; and

the computing unit controls during the replay reproduction of the stored scenario on the first representation unit starting
from the specified period of time over a remaining period of the time of the reproduction using

the stored plurality of state vectors to control reproduction of all the moveable scenario objects for at least a portion
of the reproduction,

control instructions, received during the reproduction, corresponding to an assignment of one of the plurality of moveable
objects to one of the plurality of representatives, for the reproduction of the moveable object assigned to the one of the
plurality of representatives,

wherein, in response to the assignment of the one of the plurality of moveable objects, the stored plurality of state vectors
cease to be used by the computing unit to control the reproduction of the assigned moveable object, whereby control of the
reproduction of the assigned moveable object is carried out thereafter in accordance with the control instructions.

US Pat. No. 9,506,543

ELECTROMECHANICALLY CONTROLLED DECOUPLING DEVICE FOR ACTUATORS

Airbus Defence and Space ...

1. An actuator element, comprising:
a drive unit, having a first drive element and a second drive element, wherein the first drive element and the second drive
element are arranged to functionally interact in such a manner to effect a change in length of the actuator element;

a decoupling device;
two linkage points having a span extending from one to the other of the two linkage points, wherein one of the drive elements
is connected to one of the two linkage points;

an output piston connected to the other one of the two linkage points,
wherein the span of the two linkage points in a coupled state of the decoupling device is adjustable by driving one of the
first and second drive element, and

wherein the span of the two linkage points in a decoupled state of the decoupling device is adjustable by application of an
external force on one of the two linkage points,

wherein the decoupling device comprises
a motor, a plurality of ball elements, and a sleeve element with recesses,
wherein the motor is arranged to move the sleeve element between a first position and a second position,
wherein the sleeve element is coupled with the output piston in the first position by retaining the plurality of ball elements
in corresponding recesses in the output piston, and

wherein the sleeve element is decoupled from the output piston in the second position by accommodating the plurality of ball
elements in the recesses of the sleeve element.

US Pat. No. 9,270,240

CIRCUIT LAYOUT AND METHOD FOR FREQUENCY-DEPENDENT MATCHING OF A HIGH-FREQUENCY AMPLIFIER STAGE

Airbus Defence and Space ...

1. A circuit, comprising:
a high-frequency amplifier stage, which includes a high-frequency amplifier with an input and an output, wherein the output
of the high-frequency amplifier is coupled to a total high-frequency path carrying a total frequency band;

a first partial frequency path coupled to the total high-frequency path, wherein the first partial frequency path includes
a first pass filter configured to pass a first partial frequency band,
a first matching network coupled to the first pass filter, wherein the first matching network is configured to match the high-frequency
amplifier stage in the first partial frequency band, and

a further first pass filter coupled to the first matching network, wherein the further first pass filter is configured to
pass the first partial frequency band;

a second partial frequency path coupled to the total high-frequency path, wherein the second partial frequency path includes
a second pass filter configured to pass a second partial frequency band,
a second matching network coupled to the second pass filter, wherein the second matching network is configured to match the
high-frequency amplifier stage in the second partial frequency band, and

a further second pass filter coupled to the second matching network, wherein the further second pass filter is configured
to pass the second partial frequency band; and

a coupling to an output of the first and second partial frequency paths, wherein the coupling combines an output of the first
and second partial frequency paths into the total high-frequency path,

wherein one of the first and second partial frequency paths is coupled to a control signal line that is configured to control
switching of the one of the first and second partial frequency paths,

wherein the one of the first and second partial frequency paths that is coupled to the control signal line comprises:
a first switch arranged an input the matching network of the one of the first and second partial frequency paths that is coupled
to the control signal line; and

a second switch arranged on an output side of the matching network of the one of the first and second partial frequency paths
that is coupled to the control signal line,

wherein the first and second switches are configured so that when a control signal is applied via the control signal line,
the one of the first and second partial frequency paths is shorted to ground, which reflects signals in the one of the first
and second partial frequency paths.

US Pat. No. 9,602,155

TRANSCEIVER ELEMENT FOR AN ACTIVE, ELECTRONICALLY CONTROLLED ANTENNA SYSTEM

Airbus Defence and Space ...

1. A transceiver element for an active, electronically controlled antenna system, the transceiver element comprising:
a transmit path;
a receive path;
at least first and second single-pole changeover switches with a common central connection and two connections for changing
over between the transmit path and the receive path;

a plurality of amplitude adjusters and a plurality of phase adjusters arranged between the common central connections of a
first and a second single-pole changeover switch; and

single-pole multiple-throw switches with a common central connection and a number N of connections,
wherein the common central connection of the first or second single-pole changeover switch is connected to the common central
connection of a first or a second single-pole multiple-throw switch and an amplitude adjuster and a phase adjuster are switched
in each case between each connection of the number N of connections of the first and second multiple-throw switches.

US Pat. No. 9,673,375

POWER GENERATOR WITH AN ELECTRICAL COMPONENT MADE FROM INERTIAL MASS AND CONTROL CIRCUIT THEREOF

AIRBUS DEFENCE AND SPACE ...

1. A drive circuit for a force generator for introducing vibrational forces into a structure, the drive circuit comprising:
at least one component that is a vibrating mass.
US Pat. No. 9,542,464

METHOD FOR IDENTIFYING AND CLASSIFYING AN OBJECT

Airbus Defence and Space ...

1. A method for identifying and classifying a physical object based on detected physical features of the object, comprising:
providing a multitude of derived object classes, each of which relates to a specific physical object, wherein each derived
object class is an N-dimensional vector comprising multiple binary values and each binary value is assigned to a physical
features and indicates whether or not the assigned physical feature is characteristic for the physical object of the respective
derived object class;

after provision of the multitude of derived object classes, initiating the following steps:
detecting one or more physical features of the physical object by at least one physical detector tuned for the object, and
identifying the object using an output signal of the at least one detector by:
(i) determining, using the output signal, whether the detected object possess any of a plurality of predefined physical features,
(ii) assigning a binary value to each of N predetermined basic classes based on the determination of whether the detected
object possess any of the plurality of predefined physical features, wherein the binary values indicates whether or not the
detected object possesses each of the plurality of predefined physical features,

(iii) arranging the binary values for the N basic classes in a predetermined order to form a detected object class which is
an N-dimensional vector V, wherein the detected object class is of a similar structure as a derived object class, and

(iv) classifying the object by comparing (a) the binary values for the N basic classes of the detected object with (b) binary
values for the N basic classes for the plurality of derived object classes obtained from a database, wherein each of the derived
object classes corresponds to a pre-assigned object, and wherein when the binary values for the N basic classes of the detected
object match the binary values for the N basic classes of one of the plurality of derived object classes the detected object
is identified as that object being pre-assigned to the matching one of the plurality of derived object classes.

US Pat. No. 9,255,631

TRANSMISSION OF A CONTROL FORCE

Airbus Defence and Space ...

1. A method for switching from a first transmission mode to a second transmission mode for actuation of the control component
in a vehicle, wherein for transmission of a control force is performed using a transmission device comprising a first force
transmission point, a second force transmission point, and a coupling unit disposed between the first and the second force
transmission points, wherein the coupling unit has a first side element, a second side element, and a connecting element,
wherein the first and the second side elements are each rotatably connected at one end to the first force transmission point
and are each connected at a respective other end to the connecting element at a respective first or second connection point,
wherein the first and the second connection points are spaced apart from one another on the connecting element, wherein at
least the first side element has an element configured to alter a length of the first side element between the first force
transmission point and the first connection point, and wherein the second force transmission point is provided on the connecting
element and is adjustable at least between a first and a second position, wherein the second force transmission point in the
first position is disposed in the region of the first connection point and in the second position is disposed in the region
of the second connection point, the method comprising:
a) arranging the second force transmission point in a normal setting, in which an alteration in length effected by at least
one actuator can be transmitted to the second force transmission point;

b) generating a control force by a control force generating device and transmission of the control force in a first mode,
wherein the second force transmission point is disposed in the normal setting, and wherein the control force is generated
by at least an actuator in the first side element;

c) displacing a connecting element in such a way that the second force transmission point is disposed in a redundancy setting,
in which, in event of malfunction of an actuator in one of the first or second side elements, the control force is transmittable
by the other one of the first or second side elements to the second force transmission point; and

d) generating a control force by a control force generating device and transmission of the control force in a second mode,
wherein the second force transmission point is disposed in the redundancy setting.

US Pat. No. 9,300,866

METHOD FOR IMAGE PROCESSING AND METHOD THAT CAN BE PERFORMED THEREWITH FOR THE AUTOMATIC DETECTION OF OBJECTS, OBSERVATION DEVICE AND METHOD FOR HIGH-PRECISION TRACKING OF THE COURSE FOLLOWED BY LAUNCHED ROCKETS OVER LARGE DISTANC

Airbus Defence and Space ...

1. A method for image processing, comprising:
a) collecting image data of a scene as electromagnetic radiation using an optical device;
b) processing the image data obtained in step a) using an image processing device to improve the signal-to-noise ratio of
the image data, wherein the processing involves

b1) creating a raster image by dividing a raw image that contains the image data into lines and columns;
b2) superimposing a central raster filter element of a raster filter having an odd number of lines and an odd number of columns
onto a raster image element;

b3) determining brightness values of each of the raster image elements covered by the raster filter, wherein except for the
central raster filter element, every other raster filter element has an individual light-reducing property;

b4) producing a total brightness value by summing the brightness values determined in step b3), and assigning the total brightness
value to the raster image element covered by the central raster filter element;

b5) repeating steps b2) to b4) for all remaining raster image elements; and
c) producing a result image, which has a same resolution as a raw image formed by the image data of the scene collected by
the optical device, from the total brightness values of the raster image elements obtained in step b).

US Pat. No. 10,414,116

SANDWICH COMPONENT AND METHOD FOR PRODUCING A SANDWICH COMPONENT

Airbus Defence and Space ...

1. A sandwich component, comprising:a first cover layer, a second cover layer, and a core disposed therebetween, wherein
the first and second cover layers are each formed from an outer layer made of a fiber-reinforced PEEK and, fused therewith, an inner layer made of PEI,
the core has outer layers each of which is formed from PEI, and an inner structure, which is formed entirely or partially from PEEK, and
the inner layers of the cover layers are each fused with one of the outer layers of the core with the use of an organic solvent.

US Pat. No. 9,607,790

OPERATING DEVICE WITH A PLURALITY OF ACTUATING ELEMENTS ARRANGED NEXT TO AND/OR BELOW ONE ANOTHER

Airbus Defence and Space ...

1. An operating device for an instrument panel of a vehicle, the device comprising:
a touch-screen display including a plurality of haptically indistinguishable interactive surface areas, each interactive surface
area operable as a touch-implemented actuator for operating an aspect of the vehicle;

at least one frame element including a frame surface having a plurality of consecutive sections, each section corresponding
to no more than one interactive surface area, and each interactive surface area corresponding to exactly one section,

wherein at least one section includes a haptically detectable structure, and is adjacent at least one other section not including
the haptically detectable structure, such that the haptically detectable structure provides a haptic orientation for haptically
identifying the interactive surface area,

wherein the frame element includes at least one wall projecting from the instrument panel, wherein the at least one wall is
arranged in a plane that is inclined relative to the instrument panel, and

wherein the haptically detectable structure is disposed on and extends normal to the plane of the at least one wall such that
it is disposed above one interactive surface area.

US Pat. No. 9,903,037

PROCESS FOR COATING METALLIC SURFACES WITH COATING COMPOSITIONS CONTAINING PARTICLES OF A LAYERED DOUBLE HYDROXIDE

Chemetall GmbH, Frankfur...

1. A process of increasing corrosion resistance of a corrosion resistant coating directly on a metallic surface, said process
comprising:
including in a corrosion resistant coating particles on a base of at least one layered double hydroxide (LDH) phase characterized
by the general formula [1],

[M2+(1±0.5)?x(M3+,M4+)x(OH)2±0.75]An?x/n.mH2O  [1],

wherein M2+, M3+ and M4+ are divalent, trivalent, tetravalent cations, respectively, selected from the group consisting of Ca2+, Co2+, Cu2+, Fe2+, Mg2+, Mn2+, Ni2+, Zn2+, Al3+, Ce3+, Co3+, Cr3+, Fe3+, Ga3+, V3+, Si4+, Sn4+, Ti4+ and Zr4+,

wherein one of M3+ and M4+ may be optionally absent,

wherein x is the ratio (M3++M4+)/(M2++M3++M4+) and is in a range of from 0.1 to 0.5,

wherein An? indicates an overall negative charge of intercalated species A with n being in a range of from 0.1 to 100,

wherein species A is an anion and/or a molecule including at least one anion, said anion or at least one anion being selected
from the group consisting of a hydroxide, a fluoride, a nitrate, a sulfate, a chromate, a chromite, a molybdate, a phosphomolybdate,
a phosphate, a phosphonate, a tungstate, a vanadate, an azole, a carboxylate, a dodecylbenzene, a phenolic compound, an anionic
surfactant and a biomolecule;

said particles optionally being at least one of an at least partially calcined form of said particles, an at least partially
calcined and then rehydrated form of said particles, or a totally calcined and then rehydrated form of said particles, said
particles optionally including at least one mixture of substances including an oxide, a double oxide, a multiple oxide, or
a hydroxide, at least one LDH phase, and an anion A or a molecule including at least one anion A,

wherein said metallic surface is an iron-based substrate or an aluminium alloy.

US Pat. No. 9,565,723

DEVICE AND METHOD FOR GENERATING LIGHT OF A PREDETERMINED SPECTRUM WITH AT LEAST FOUR DIFFERENTLY COLORED LIGHT SOURCES

Airbus Defence and Space ...

1. A lighting device comprising:
a lighting unit comprising at least four light sources, each light source having a different color spectra;
a color rendering index calculation unit to calculate a color rendering index based on stored data on spectra of the light
sources and individual first drive data for the light sources;

a drive unit to individually energize the light sources of the lighting unit according to the individual first drive data;
a sensor to measure a spectral power distribution emitted by the lighting unit;
a control unit configured to:
receive the spectral power distribution, a predetermined spectral power distribution, and the color rendering index associated
with weighted sensor values calculable from the individual first drive data;

maximize the color rendering index according to a condition that an error between the predetermined spectral power distribution
and the measured spectral power distribution is smaller than a limit value;

determine individual second drive data based on the color rendering index as maximized; and
act on the drive unit such that the light sources of the lighting unit are individually energized according to the individual
second drive data.

US Pat. No. 9,535,251

HMD APPARATUS WITH ADJUSTABLE EYE TRACKING DEVICE

Airbus Defence and Space ...

1. A head-mounted display (HMD) apparatus comprising: an imaging optical system for an eye of a user, the imaging optical
system comprising a display unit to be viewed by the eye of the user, and a control device to acquire a viewing direction
of the eye of the user within a field of view of the display unit using an eye camera;
a camera holder to receive the eye camera, the camera holder being selectively adjustable in relationship to the display unit
to vary an orientation of the eye camera in terms of a peripheral angle around a viewing central axis of the field of view
and in terms of a setting angle with respect to the viewing central axis;

a peripheral position ring that surrounds the field of view; and
a setting angle unit for different setting angles, the camera holder mountable detachably on the setting angle unit to selectively
adjust the setting angle, the setting angle unit mountable detachably on the peripheral position ring and adjustable in discrete
notch steps along the peripheral position ring to selectively adjust the peripheral angle.

US Pat. No. 9,630,716

CARGO RESTRAINING BARRIER, CARGO LOADING SYSTEM AND AIRCRAFT

Airbus Defence and Space ...

1. A cargo restraining barrier configured to be mounted to a cargo deck surface of an aircraft, the cargo restraining barrier
comprising:
a base portion having a top side and a bottom side opposite to the top side;
a barrier portion being arranged substantially perpendicular to the base portion at a first edge on the top side of the base
portion;

a plurality of force diverting struts being mounted in parallel along the extension of the base portion between a backside
of the barrier portion and a second edge of the base portion opposite to the first edge of the base portion, the force diverting
struts being configured to divert forces acting on the front side of the barrier portion towards the base portion; and

a plurality of first latches distributed over the bottom side of the base portion, the first latches being configured to hook
into tie down rings of a cargo deck surface and to direct the diverted forces from the force diverting struts into the cargo
deck surface.

US Pat. No. 9,851,724

AUTOMATIC TAKE-OFF AND LANDING CONTROL DEVICE

Airbus Defence and Space ...

1. An automatic take-off and landing control device for an aircraft, the control device comprising:
at least one of a radar-based tracking device or a pseudo-lite system based tracking device, the radar-based tracking device
and the pseudo-lite system based tracking device being adapted for receiving at least one local signal from at least one local
ground station and for determining a position of the aircraft based on the at least one local signal, and at least one of:

at least one GNSS tracking device adapted for receiving a GNSS signal and for determining a position of the aircraft based
on the GNSS signal,

at least one camera device adapted for observing an environment of the aircraft and for determining a position of the aircraft
based on the camera signal;

at least one monitoring device adapted for continuously supervising a performance and a health status of the at least one
radar-based or pseudo-lite system based tracking device based on analyzing signals received from the radar-based or pseudo-lite
system based tracking device, one of the at least one GNSS tracking device, and the at least one camera device; and

wherein the camera device is adapted for determining the position of the aircraft if the local tracking device and the GNSS
tracking device are unavailable.

US Pat. No. 9,672,171

ACCESS CONTROL TO A JOINTLY EXCLUSIVELY USABLE TRANSMISSION MEDIUM

Airbus Defence and Space ...

1. A computing system having a plurality of components which use a resource exclusively jointly, wherein each component is
configured to use the resource and at one given point of time only one component can use the resource, the computing system
comprising:
an activity monitoring unit configured to record a number of activities of a component on the resource; and
an interrupting unit configured to interrupt access of the component for use of the resource when the number of activities
of the component recorded by the activity monitoring unit reaches an activity threshold, so that an assignment strategy can
reassign the exclusively jointly used resource to any one of requesting components,

wherein the requesting components include the component which was interrupted by the interrupting unit and remaining components
of the plurality of components, each of the plurality of components having an individually adapted activity threshold, and

wherein the interrupting unit is configured to indirectly affect assignment of the resource to a component by the assignment
strategy as a result of interrupting the component which is currently using the resource.

US Pat. No. 9,632,078

DETECTION OF ANTIGENS

AIRBUS DEFENCE AND SPACE ...

1. A method for the detection of at least one antigen in a sample comprising the steps of:
(a) coating magnetic beads with at least one antibody specific for the at least one antigen;
(b) washing the coated beads with a first washing solution comprising a buffer and about 8% to 12% bovine serum albumin (BSA);
(c) incubating the washed beads with the sample to form a mixture;
(d) washing the mixture with a second washing solution comprising a buffer;
(e) isolating the beads using a magnetic separator; and
(f) detecting the at least one antigen in the sample.

US Pat. No. 9,592,904

DRIVE MECHANISM FOR A DEFORMABLE STRUCTURE, STRUCTURAL COMPONENT PROVIDED THEREWITH AND FLOW BODY AND LIFT-ASSISTING DEVICE

AIRBUS DEFENCE AND SPACE ...

1. A drive mechanism for deforming a skin of a deformable structural component of a fluid-dynamic flow body, the drive mechanism
comprising:
a linearly movably driven linear movement unit configured to move linearly in a linear movement direction; and
a transmission element comprising a translation lever having a first end pivotally coupled at the linear movement unit about
a first pivot axis transverse to the linear movement direction and a second end, opposite to the first end, pivotally coupled
at a rotatable mounted load introduction device about a second pivot axis transverse to the linear movement direction, the
translation lever being configured to translate the linear movement of the linear movement unit into second end linear movement
of the second end of the translation lever, the second end linear movement being transverse to the linear movement of the
linear movement unit and generating rotary movement of the rotatably mounted load introduction device to introduce a deformation
force onto the skin of the structural component.

US Pat. No. 9,828,174

METHOD AND SYSTEM FOR MONITORING THE INTEGRITY OF FREIGHT CONTAINERS

Airbus Defence and Space ...

1. A method for monitoring the integrity of one or more freight containers along a transport route, wherein at least one freight
container has a monitoring device (10) associated therewith that has at least one monitoring sensor (12) monitoring the integrity of the freight container, comprising:
sensing of an event violating the freight container integrity by the monitoring sensor (12);

transmitting event data, representing the integrity violation, to an analysis device (18) associated with an analysis center (14),

wherein the analysis device (18) associated with the analysis center (14) rates the transmitted event data using predetermined criteria in respect of either a sanctioned or authorized or an unsanctioned
or unauthorized integrity violation of the freight container, and

wherein opening or closing of the freight container is rated as a sanctioned or authorized integrity violation if an electronic
authorization code representing the sanction for the opening operation or the closing operation is sent to the analysis center
(14) for the event data representing this integrity violation; and

distinguishing different types of opening operations and/or different types of closing operations by using respective authorization
function codes from different function groups, as result of which the analysis center (14) uses the type of the respectively received function code to determine what type of opening operation and/or what type of
closing operation has taken place or is meant to take place.

US Pat. No. 9,754,498

FOLLOW-ME SYSTEM FOR UNMANNED AIRCRAFT VEHICLES

Airbus Defence and Space ...

1. A system for navigating an aircraft, comprising:
a first aircraft with a first communication unit; and
a second aircraft with a second communication unit,
wherein the first aircraft is adapted to determine coordinates of a position of a waypoint,
wherein the first communication unit is adapted to transmit the coordinates of the position of the waypoint to the second
communication unit, and

wherein the second aircraft is adapted to navigate to the position of the waypoint,
the first aircraft further comprising:
a first processing unit,
wherein the first processing unit is adapted to determine a position of the second aircraft based on a signal sent from the
second communication unit to the first communication unit.

US Pat. No. 9,845,163

DISPLAY ASSEMBLY, USE OF A DISPLAY ASSEMBLY, AND AIRCRAFT ASSEMBLY HAVING SUCH A DISPLAY ASSEMBLY

Airbus Defence and Space ...

1. A display assembly for displaying a parameter of an aircraft, comprising:
a parameter device for gathering a parameter of at least one of the aircraft or an equipment of the aircraft, including a
sending unit for sending the parameter; and

a detachable non-transparent display device, configured to display the parameter, and comprising a receiving unit for receiving
the parameter;

a work clothing for an operator of the aircraft to which the display device is attached,
a plurality of display components arranged at different positions of the work clothing and the aircraft so that a display
for the parameter is always in a field of view of a pilot or the operator;

wherein the sending unit is configured to transmit the parameter directly to the receiving unit.

US Pat. No. 9,809,324

LIGHTNING PROTECTION LAYER FOR FIBER COMPOSITE STRUCTURES

Airbus Defence and Space ...

1. A lightning protection layer for an aircraft, comprising:
a first stratum;
a second stratum, which is coupled with the first stratum along a connecting surface; and
a third stratum which is arranged such that the first stratum is disposed between the second stratum and the third stratum,
wherein the first stratum has a metal foil,
wherein the second stratum has at least one two-dimensional flat graphene later,
wherein the third stratum has at least one two-dimensional flat graphene layer.

US Pat. No. 9,784,613

SENSOR FOR DETECTING AND LOCALISING LASER BEAM SOURCES

Airbus Defence and Space ...

1. A sensor for detecting and localizing laser radiation sources, comprising:
a radiation-sensitive detector arranged in an image field of an imaging optical unit;
an electronic image processing device coupled to the radiation-sensitive detector; and
an optical diffraction element arranged in a beam path, wherein
diffraction properties of the optical diffraction element are designed such that incident laser light in different wavelength
bands produces diffraction patterns of different forms, wherein the different forms of the diffraction patterns that are associated
with individual wavelength bands differ by way of a rotation about a same axis of rotation,

the electronic image processing device is configured to detect and evaluate the different forms of the diffraction patterns,
and

the diffraction properties of the optical diffraction element are configured such that:
a size of the diffraction pattern at a maximum wavelength of a wavelength band is substantially the same for all wavelength
bands, and

a size of the diffraction pattern at a minimum wavelength of a wavelength band is substantially the same for all wavelength
bands.

US Pat. No. 9,625,145

HIGH FREQUENCY-STABILIZED COMBUSTION IN AIRCRAFT GAS TURBINES

Airbus Defence and Space ...

1. A gas turbine, comprising:
a combustion chamber with a cavity configured to receive and burn a fuel-air mixture, wherein the combustion chamber is an
annular combustion chamber that extends annularly about a rotational axis of the gas turbine; and

a microwave source configured to produce microwave radiation,
wherein the gas turbine is configured to guide the microwave radiation into the cavity of the combustion chamber to support
the combustion of the fuel-air mixture in the combustion chamber,

wherein the gas turbine comprises an annular first chamber attached to the combustion chamber, so as to be disposed outside
of the combustion chamber from a perspective of the rotational axis of the gas turbine, and extending annularly about the
rotational axis of the gas turbine,

wherein an annular second chamber is disposed inside the first chamber, and extending annularly about the rotational axis
of the gas turbine,

wherein a plurality of microwave-permeable windows is included in a limiting surface between the combustion chamber and the
second chamber and are arranged annularly about the rotational axis of the gas turbine,

wherein the second chamber has a plurality of slits that are arranged annularly about the rotational axis of the gas turbine
and opposing the microwave-permeable windows, and

wherein the microwave source is connected to an antenna that projects into the first chamber.

US Pat. No. 9,623,619

CONNECTION ARRANGEMENT FOR CONNECTING TWO PROFILED ELEMENTS IN AN AERODYNAMICALLY SMOOTH MANNER, METHOD FOR PRODUCING SAID CONNECTION ARRANGEMENT, AND DEVICE FOR CARRYING OUT THE METHOD

Airbus Defence and Space ...

1. A method of forming a connection arrangement that connects two profiled elements in a seamless and aerodynamically smooth
manner, the connection arrangement forming a profiled surface around which laminar flow is possible, the method comprising:
providing a first profiled element that has a first fixing strip with first bore holes with fixing bolts, the first fixing
strip defining a surface;

providing a second profiled element that has a second fixing strip arranged beneath the first fixing strip, the second fixing
strip has second bore holes aligned with the first bore holes that receive the fixing bolts to rigidly connect the first profiled
element to the second profiled element, the surface of the first fixing strip disposed lower than surfaces of the first profiled
element and the second profiled element to define a filler region above the surface of the first fixing strip surface;

partially filling the filler region with a first filling material layer, smoothing a surface of the first filling material
in a longitudinal direction of the connection arrangement, and curing the first filling material layer; and

completely filling the filler region with a second filling material layer, smoothing a surface of the second filling material
layer in a shaping manner, and curing the second filling material layer to form the profiled surface that connects the surfaces
of the first profiled element and the second profiled element.

US Pat. No. 9,725,173

DETACHABLE CONNECTING ARRANGEMENT FOR FITTING LAUNCHABLE EXTERNAL LOADS TO AN AIRCRAFT

Airbus Defence and Space ...

1. A detachable connecting arrangement for fitting a launchable external load to an aircraft, the detachable connecting arrangement
comprising:
a connecting element configured for connection to the external load; and
a holding element configured for connection to the aircraft and to the connecting element,
wherein the connecting element includes at least one lower supporting surface and at least one upper supporting surface;
wherein the holding element includes at least one first opposing supporting surface that is configured to interact with the
at least one lower supporting surface of the connecting element, and at least one second, upper opposing supporting surface
that is configured to interact with the at least one upper supporting surface of the connecting element,

wherein the at least one lower supporting surface of the connecting element and the at least one first opposing supporting
surface of the holding element are configured to support mass forces of the external load directed away from the aircraft,

wherein the at least one upper supporting surface of the connecting element and the at least one second, upper opposing supporting
surface of the holding element are configured to support mass forces of the external load directed towards the aircraft,

wherein the connecting element comprises a fastening shaft for connection to the external load at a lower end of the fastening
shaft, the fastening shaft having a projecting nose at an upper end,

wherein the at least one lower supporting surface of the connecting element is arranged on a bottom of the projecting nose
of the fastening shaft, the bottom of the projecting nose facing towards the lower end of the fastening shaft,

wherein the holding element has a first recess that is configured to engage the projecting nose of the fastening shaft,
wherein the first recess opens towards a back side of the holding element,
wherein the at least one first opposing supporting surface of the holding element is arranged in an area of a floor of the
first recess being oriented towards the back side of the holding element, and

wherein the at least one lower supporting surface of the connecting element and the at least one first opposing supporting
surface of the holding element are curved in a circular arc.

US Pat. No. 9,696,373

VERIFICATION AND CERTIFICATION OF AN ELECTRONIC COMPONENT

Airbus Defence and Space ...

1. A circuit configured to be executed in a predeterminable operating mode of a plurality of operating modes, the circuit
comprising:
a first functional unit;
a second functional unit;
wherein the first functional unit is configured as a static functional unit configured, in each of the plurality of operating
modes of the circuit, to carry out a consistent function;

wherein the second functional unit is configured as an adaptable functional unit configured, prior to the circuit being put
into service, according to a first configuration of a plurality of different configurations;

wherein the second functional unit is configured, during the operating time of the circuit, to maintain the first configuration
so that the first configuration of the second functional unit defines the predeterminable operating mode of the circuit; and

wherein the static functional unit is configured to carry out the same function in each of the plurality of operating modes
of the circuit;

wherein the adaptable functional unit is configured to carry out a different function in each of the plurality of operating
modes of the circuit;

wherein the circuit is configured to enable distinguishing between static functions and dynamic functions and to determine
which of the dynamic functions are known and already verified and which are not known and not verified yet; and

wherein the circuit enables verification of only those dynamic functions which are not known.

US Pat. No. 9,764,815

AIRCRAFT FUSELAGE STRUCTURE

Airbus Defence and Space ...

1. An aircraft fuselage structure extending along a longitudinal axis, the fuselage structure comprising an outer skin which
surrounds an internal space, comprising a plurality of circumferential ribs which are spaced apart from one another and which
extend in planes perpendicular to the longitudinal axis along the outer skin, wherein a recess is provided for receiving a
wing torsion box in the outer skin, the recess extending in a direction of the longitudinal axis via a plurality of ribs from
a front transverse edge to a rear transverse edge, wherein the recess extends in a circumferential direction from a vertical
longitudinal central plane symmetrically on both sides as far as longitudinal edges extending parallel to the longitudinal
axis and wherein the ribs are interrupted in a region of the recess, and wherein:
first longitudinal members are provided, the first longitudinal members being adjacent to the recess and extending along the
longitudinal edges beyond an entire length of the recess,

end regions of the first longitudinal members are connected to ribs which extend circumferentially at intervals from the transverse
edges of the recess along the outer skin over the vertical longitudinal central plane,

ends of the ribs facing the recess are connected to the first longitudinal members,
second longitudinal members are provided, the second longitudinal members extending parallel and at intervals from the first
longitudinal members and being arranged on the side of the first longitudinal members facing away from the recess, and

end regions of the second longitudinal members are connected to ribs which extend circumferentially at intervals from the
transverse edges of the recess along the outer skin over the vertical longitudinal central plane.

US Pat. No. 9,728,094

REDUNDANT DETERMINATION OF POSITIONAL DATA FOR AN AUTOMATIC LANDING SYSTEM

Airbus Defence and Space ...

1. An automatic landing system for an aircraft, comprising:
a control device configured to provide positional data for controlling the aircraft;
a first position or range measuring device configured to detect first positional data of the aircraft;
a second position or range measuring device configured to detect second positional data of the aircraft; and
a sensor device configured to detect sensor data from which at least one of a direction in which a landmark is located and
a range of the landmark to the aircraft can be determined,

wherein the control device is configured to generate a first hypothesis for the determined direction or range of the landmark
on the basis of the first positional data and a second hypothesis for the determined direction or range of the landmark on
the basis of the second positional data,

wherein the control device is configured to either confirm or discard the first hypothesis and the second hypothesis, respectively,
using the sensor data detected by the sensor device, and

wherein the control device is configured to determine that only positional data, on which a confirmed hypothesis is based,
is to be used to control the aircraft.

US Pat. No. 9,692,625

METHOD TO INCREASE DATA RATE/ROBUSTNESS BY USING TERNARY PRECODED SIGNALS FOR TRANSMISSION

Airbus Defence and Space ...

1. A method for modulation of a signal with first binary data, wherein the first binary data include a sequence of first binary
numbers, wherein each first binary number comprises either a first binary numerical value or a second binary numerical value,
and wherein the method comprises:
generating ternary data that includes a sequence of ternary numbers, wherein each ternary number comprises a first, second,
or third ternary numerical value, and

modulating a phase of the signal with the ternary data, wherein the phase of the signal can assume M different phase states,
where M>2, and wherein the first, second, and third ternary numerical values correspond to first, second, and third state
transitions between the M phase states,

wherein in the first state transition, a phase state is maintained, and the second state transition and third state transition
produce a change in the phase state,

wherein generating ternary data comprises generated the ternary data such that:
all first binary numbers with the first binary numerical value are allocated to ternary numbers with the first ternary numerical
value, and

all first binary numbers with the second binary numerical value are allocated to ternary numbers with the second or third
ternary numerical value so that in the sequence of ternary numbers, the second ternary numerical value does not directly follow
the third numerical value and vice versa.

US Pat. No. 9,772,295

LAYING HEAD, FIBRE PLACEMENT DEVICE AND METHOD

Airbus Defence and Space ...

1. A laying head for a fibre placement device, comprising:
a placing roller which is permeable to laser light, at least in part;
a laser light feed unit which is arranged in an inner space of the placing roller; and
a sensor which is designed and arranged to receive laser light reflected from a component on which the placing roller places
a fibre band.

US Pat. No. 9,725,790

PROCESS FOR PRODUCING AN ALUMINUM-SCANDIUM-CALCIUM ALLOY

Airbus Defence and Space ...

1. A method for adding calcium to an aluminum-scandium-magnesium-zirconium alloy for producing an aluminum-scandium-magnesium-zirconium-calcium
alloy, the method comprising the steps:
a) combining aluminum, scandium, magnesium, zirconium and calcium together in a common melt; and
b) quenching the common melt by a rapid solidification process at a speed of more than 1000 K/s,
wherein the calcium is added to the alloy in a ratio so that a density less than 2.6 g/cm3 is achieved, and

wherein step a) comprises combining 0.2 wgt.-% to 3 wgt.-% scandium; 1.0 wgt.-% to 8.0 wgt.-% magnesium; 0.1 wgt.-% to 1.5
wgt.-% zirconium; 0.5 wgt.-% to 5 wgt.-% calcium; and a remainder being aluminum and undesirable contaminants together in
the common melt.

US Pat. No. 9,774,077

ELECTROMAGNETIC HIGHLY TRANSPARENT RADOME FOR MULTI-BAND APPLICATIONS AND WIDEBAND APPLICATIONS

AIRBUS DEFENCE AND SPACE ...

1. A radome for shielding a transmitter/receiver unit, comprising:
a wall forming a window portion having a core layer, a first cover layer and a second cover layer arranged so that the first
cover layer and the core layer and the second cover layer and core layer are mechanically connected to one another in such
a manner that the core layer is arranged between the first cover layer and the second cover layer,

wherein the first cover layer and the core layer are arranged such that a surface of the first cover layer is, at least in
sections, adjacent to a first surface of the core layer, and the second cover layer and the core layer are arranged such that
a surface of the second cover layer is, at least in sections, adjacent to a second surface of the core layer,

wherein the first cover layer comprises at least a first partial layer, a second partial layer and a third partial layer,
the first partial layer being arranged such that it forms a first surface of the wall, the second partial layer being arranged
between the first partial layer and the third partial layer, and the first partial layer and the third partial layer having
higher dielectric constants than that of the second partial layer, and

wherein the second cover layer comprises at least a fourth partial layer, a fifth partial layer and a sixth partial layer,
the fourth partial layer being arranged such that it forms a second surface of the wall, the fifth partial layer being arranged
between the fourth partial layer and the sixth partial layer, and the fourth partial layer and the sixth partial layer having
higher dielectric constants than that of the fifth partial layer.

US Pat. No. 10,027,113

HIGH-VOLTAGE DC VOLTAGE UNIT AND METHOD FOR OPERATING A HIGH-VOLTAGE DC VOLTAGE UNIT

Airbus Operations GmbH, ...

1. An aircraft having a high-voltage DC voltage unit, the high-voltage DC voltage unit, comprising:a first DC voltage apparatus which is configured to provide a first high-voltage DC voltage between a first output connection and a second output connection of the first DC voltage apparatus or is configured to be fed with a first high-voltage DC voltage;
a second DC voltage apparatus which is configured to independently provide a second high-voltage DC voltage between a first output connection and a second output connection of the second DC voltage apparatus or is configured to be fed with an independent second high-voltage DC voltage;
a first DC voltage connection which is coupled with the first output connection of the first DC voltage apparatus;
a second DC voltage connection which is coupled with the second output connection of the second DC voltage apparatus; and
a reference potential connection which is coupled with the second output connection of the first DC voltage apparatus, with the first output connection of the second DC voltage apparatus and with an earth potential, wherein the first and second high-voltage DC voltages realise a bipolar power supply.

US Pat. No. 9,863,398

WIND-POWERED ROTOR AND ENERGY GENERATION METHOD USING SAID ROTOR

Airbus Defence and Space ...

1. A wind power rotor, comprising:
a first rotor device that rotates about a first axis of rotation and has at least two rotor blades that move on a peripheral
track about the first axis of rotation, wherein the at least two rotor blades are arranged in such a manner that they define
a virtual first shell surface of a virtual first rotating body upon rotation about the first axis of rotation; and

a second rotor device that rotates about a second axis of rotation and has a second rotating body with a closed second shell
surface, wherein the second rotating body is arranged at least partially inside of the virtual first rotating body,

wherein the first rotor device is driven by wind in a first direction of rotation to convert wind energy into a drive force,
and the second rotor device is driven in a second direction of rotation running counter to the first direction of rotation,

wherein, of the first and second rotor devices, only the first rotor device is driven by wind by virtue of the closed second
shell surface, and

wherein the second rotor device produces a deflection of an air stream caused by the wind inside of the first rotor device
against the first direction of rotation on a side of the second rotor device facing away from the wind.

US Pat. No. 10,071,817

INDICATION BOLT FOR MONITORING ADHESIVE BONDS IN STRUCTURAL ELEMENTS

Airbus Defence and Space ...

1. A structural element, comprising:a first component and a second component;
a bonded joint, by which the first component and the second component are interconnected; and
an indication bolt, which is fixed to the first component and the second component,
wherein the indication bolt is designed to indicate when the first component and the second component have moved relative to one another,
wherein the indication bolt has a predetermined breaking point, which deforms under a predetermined loading of the indication bolt introduced by the relative movement of the first and second component or breaks under the predetermined loading of the indication bolt introduced by the relative movement of the first and second component to detect whether the relative movement of the first component and the second component has taken place,
wherein the predetermined breaking point is a narrowed region adjacent to a head of the indication bolt.

US Pat. No. 9,757,879

FIBRE APPLIANCE TOOL, FIBRE PLACEMENT DEVICE, FIBRE PLACEMENT METHOD, AND PRODUCTION METHOD

Airbus Defence and Space ...

1. A fiber application tool for a fiber application process having a fiber contact surface area, which has a fiber contact
surface for contacting fibers for the purpose of redirecting and/or pressing fibers for application onto a work surface and
having an activation device for activating, by means of an activation radiation, an adhesive, matrix, resin, or binder material
provided at the fibers, such that the fibers are tacked onto the work surface,
wherein the fiber contact surface area is transparent for the activation radiation and that the activation device is configured
to guide and/or deliver the activation radiation through the transparent fiber contact surface area to the fibers to be pressed
by the fiber contact surface,

wherein the fiber contact surface area is formed at a circumference of a fiber application and/or compaction roller,
wherein at least one circumferential surface area of the fiber application and/or compaction roller has the fiber contact
surface configured in a transparent manner, and

wherein the activation device is configured to guide the activation radiation starting from an interior of the fiber application
and/or compaction roller through the transparent circumferential surface area to the fibers, which contact the fiber contact
surface area according to a specified use.

US Pat. No. 9,753,143

AIRCRAFT NAVIGATION SYSTEM AND METHOD OF NAVIGATING AN AIRCRAFT

AIRBUS DEFENCE AND SPACE ...

1. An aircraft navigation system for an unmanned aircraft comprising:
a civil-certified GPS-receiver,
a military-type GPS-receiver, and
a control device provided by a computer, the control device including a monitoring unit and an alerting unit,
wherein the civil-certified GPS-receiver is configured to determine a first position information based on civil course/acquisition
code GPS signals (C/A-GPS-signals),

wherein the military-type GPS-receiver is configured to determine a second position information based on military precision
code or encrypted precision code GPS signals (P(Y)-GPS-signals),

wherein the aircraft navigation system is configured to issue aircraft navigation signals based on the first position information
when the aircraft is flying under civil-certified navigation control in civil airspace,

wherein at least one of:
the monitoring unit is configured to detect jamming of the C/A-GPS-signals, or
the monitoring unit is further configured to compare the first position information with the second position information,
and to detect an occurrence of a difference between the first position information and the second position information being
larger than a threshold value for more than a threshold duration, and

wherein the alerting unit is configured to initiate an alert procedure upon detection of at least one of the jamming of the
C/A GPS signals and the occurrence of the difference between the first position information and the second position information
being larger than a threshold value for more than a threshold duration.

US Pat. No. 10,047,465

METHOD FOR MANUFACTURING A FIBER COMPOSITE COMPONENT

Airbus Defence and Space ...

1. A method for manufacturing a fiber composite component comprising:a) providing a fiber material with a separating foil on a surface area;
b) introducing at least one thread into at least one partial area of the fiber material, such that the thread undulates as the thread extends along the surface area of the fiber material, such that sections of the thread alternately run inside of the fiber material and outside of the fiber material;
c) infiltrating the fiber material with a curable matrix material;
d) curing the matrix material; and
e) peeling away the separating foil from the fiber material, so that the thread loops are free of the matrix material.

US Pat. No. 10,116,011

SWITCHING DEVICE FOR AN ELECTROCHEMICAL ENERGY STORE AND ENERGY STORAGE SYSTEM

Airbus Defence and Space ...

1. A switching device for an electrochemical energy store, with: a film transistor device, which includes at least one organic transistor and which is attachable in planar manner to at least one electrode of the electrochemical energy store, and which is controllable by an external voltage source and is configured as a controllable electrical resistor in series with an in internal resistance of the electrochemical energy store.

US Pat. No. 10,035,607

ELECTRICAL DRIVE SYSTEM FOR AN AIRCRAFT AND OPERATING METHOD

Airbus Defence and Space ...

1. An electrical drive system for an aircraft, comprising:at least one first and one second electrical direct voltage source for supplying a direct voltage,
a first electrical machine module and a second electrical machine module, the electrical machine modules being configured to convert electrical alternating voltage into mechanical movement and/or to convert mechanical movement into electrical alternating voltage, the first electrical machine module being connected to a first power inverter and the second electrical machine module being connected to a second power inverter, the first and second power inverters being connected in series and the first and the second direct voltage sources being connected in series to generate an overall direct voltage to which the series-connected power inverters are connected, the power inverters each having one voltage measuring device for measuring the power inverter direct voltage present at the respective power inverter and a power inverter control device for controlling the operation of the power inverters in accordance with the power inverter direct voltage, a compensating line being provided between a voltage source center tap between the first and second voltage sources and a power inverter center tap between the first and second power inverters, and the first and second power inverter control devices being connected to each other communicatively by a communication device to exchange at least one piece of information about the measured power inverter direct voltages in real time; and
a compensating current measuring device for measuring the compensating current flowing through the compensating line, wherein a piece of information about the measured compensating current is configured to be transmitted via the communication device to at least one of the power inverter control devices.

US Pat. No. 10,071,799

COOPERATIVE ACTUATOR SYSTEM FOR ACTIVE FLOW CONTROL

AIRBUS DEFENCE AND SPACE ...

1. A cooperative actuator system for active flow control along a surface, comprising:a plurality of actuators;
a control unit; and
a data unit;
wherein the plurality of actuators are configured to be distributed along the surface in at least a first group and a second group downstream of the first group,
wherein the control unit is configured to control the actuators of the first group so that they form a first flow structure along the surface,
wherein the data unit is configured to provide data of the first flow structure,
wherein the control unit is further configured to control the actuators of the second group based on the data of the first flow structure, so that the actuators of the second group cooperatively interact with the first flow structure to form a second flow structure along the surface, and
wherein the plurality of actuators are fluidic actuators configured to influence the first flow structure and the second flow structure by introducing air into or sucking air off a surrounding flow.

US Pat. No. 10,100,446

MODULE ELEMENT FOR DRIVING AND RETAINING BRAIDING BOBBIN CARRIERS AND A BRAIDING DEVICE

Airbus Defence and Space ...

1. A braiding device for braiding fibrous semifinished products, the braiding device comprising:a plurality of module elements for driving and retaining braiding bobbin carriers on a predetermined bobbin path, each of the module element comprising
a base element that is rotatable about an axis of rotation; and
a retaining element integrally formed with the base element,
wherein the retaining element releasably holds at least one braiding bobbin carrier offset from the axis of rotation using a first electromagnet,
wherein the plurality of module elements are arranged relative to each other such that at least one first retaining element of a first module element transfers the braiding bobbin carriers to a second retaining element of a second module element along the predetermined bobbin path, wherein the transfer occurs by suspending a magnetic field of the first electromagnet.

US Pat. No. 10,426,021

MICROELECTRONIC MODULE FOR ALTERING THE ELECTROMAGNETIC SIGNATURE OF A SURFACE, MODULE ARRAY AND METHOD FOR ALTERING THE ELECTROMAGNETIC SIGNATURE OF A SURFACE

Airbus Defence and Space ...

1. A microelectronic module for altering an electromagnetic signature of a surface, comprising:at least one voltage converter for converting a first voltage provided into a higher, lower or identical second voltage; and
at least one actuator, comprising at least one generator configured for generating an electrical plasma from the second voltage provided by the voltage converter;
wherein at least the voltage converter and the actuator are arranged on a thin-layered planar substrate; and
wherein the electromagnetic signature is altered by an interaction of the electrical plasma generated by the actuator with an electromagnetic radiation impinging on the surface; and
wherein the at least one actuator is configured to generate the electrical plasma with a specific frequency band selected for altering the electromagnetic radiation.

US Pat. No. 10,086,941

MULTIFUNCTIONAL POD FOR AN AIRCRAFT

Airbus Defence and Space ...

1. Aircraft having a multifunctional pod which is releasably fastenable to the aircraft, comprising:at least two separate regions;
at least one first region of the at least two separate regions being provided for receiving fuel, wherein the first region for receiving fuel is arranged in a front region of the pod; and
at least one second region of the at least two separate regions comprising at least one receiving device for releasably attaching at least one additional load,
the additional load being configured to be releasably attachable to the at least one receiving device via a loading opening on the side of the pod facing away from the aircraft,
wherein a third region for receiving fuel is arranged in the rear region of the pod,
wherein the second region is arranged between the first region and the third region in a lengthwise direction of the pod, and wherein the multifunctional pod is releasable from the aircraft during flight, and
wherein the at least one first region and the third region, on the side of the pod facing the aircraft, extend into the at least one second region at least in part.

US Pat. No. 9,963,219

AIRFOIL PORTION WITH A CHAMBER

Airbus Defence and Space ...

1. An airfoil portion, comprising:an outer skin member;
an inner stiffening member, and
a flow control system configured to provide an air flow relative to a surface of the airfoil portion, the flow control system comprising at least one fluidic actuator with an actuator stage and a control stage separated by a cover panel for influencing the air flow relative to the surface,
wherein at least one of the outer skin member and the inner stiffening member is arranged to at least partially delimit a chamber,
wherein the chamber is configured to contain an inner pressure,
wherein the inner pressure differs from a pressure external to the chamber,
wherein the actuator stage is mounted to the inner stiffening member,
wherein the cover panel and the control stage are mounted to the actuator stage, and
wherein the actuator stage, the cover panel and the control stage form a load carrying structure.

US Pat. No. 9,980,327

DEVICE AND METHOD FOR GENERATING LIGHT OF A PREDETERMINED SPECTRUM WITH A PLURALITY OF DIFFERENTLY COLORED LIGHT SOURCES

Airbus Defence and Space ...

1. A lighting device comprising:a lighting unit comprising a plurality of light sources, each light source having a different color spectra;
a color rendering index calculation unit to calculate a color rendering index based on stored data on spectra of the light sources and individual first drive data for the light sources, wherein in calculating the color rendering index, the color rendering index calculation unit is configured to:
use a function between a respective maximum of a spectrum and a radiation intensity to determine a multiplication factor from which a radiation spectrum of a light source at a current light source drive value is determined;
add radiation spectra of all the light sources into a virtual total radiation spectrum; and
determine the color rendering index from the virtual total radiation spectrum;
a drive unit to individually energize the light sources of the lighting unit according to the individual first drive data;
a sensor to measure a spectral power distribution emitted by the lighting unit; and
a control unit configured to:
receive the spectral power distribution, a predetermined spectral power distribution, and the color rendering index associated with weighted sensor values calculable from the individual first drive data;
maximize the color rendering index associated with the weighted sensor values calculable from the individual first drive data; and
stop maximization when an error between the predetermined spectral power distribution and the spectral power distribution as measured falls below a limit value.

US Pat. No. 9,963,241

AIRPLANE WITH A FUEL CELL DEVICE

Airbus Defence and Space ...

1. An aircraft comprising:an ambient air inlet to intake and purify ambient air;
a cryogenic container comprising a hydrogen tank and a superconducting magnetic energy storage unit (SMES unit), the hydrogen tank to store liquid hydrogen, the SMES unit to store electrical energy; and
a fuel cell device connected to the ambient air inlet by an air supply line and to the hydrogen tank of the cryogenic container by a hydrogen supply line, the fuel cell device to supply the electrical energy from a reaction of the liquid hydrogen and oxygen of the ambient air to the SMES unit of the cryogenic container, wherein the cryogenic container does not have an additional cooling system or an additional liquid hydrogen generating device, and wherein the cryogenic container is dimensioned so that the hydrogen tank stores a maximum of 40 kg liquid hydrogen.

US Pat. No. 9,944,398

AIRCRAFT SUPPLEMENTARY COOLING SYSTEM BY EVAPORATING LIQUID NITROGEN

AIRBUS DEFENCE AND SPACE ...

1. A cooling system for an interior space of a vehicle, comprising:a main cooling system coupled to an air inlet for receiving air and coupled with the interior space for providing cooled air to an interior space;
at least one air duct arranged between the air inlet and the interior space;
a reservoir for liquid nitrogen having a nitrogen outlet; and
a valve arranged between the nitrogen outlet of the reservoir and an injection port of the at least one air duct;
wherein the main cooling system is an evaporative cooling system comprising at least one heat exchanger arranged in the air inlet or an air cycle cooling system;
wherein the reservoir is couplable with the injection port of the at least one air duct via the valve on demand for evaporating nitrogen in the at least one air duct; and
wherein the injection port is upstream of the main cooling system, and downstream of the air inlet.

US Pat. No. 9,887,349

COATING METHOD, SURFACE LAYER STRUCTURE, AS WELL AS APPLICATIONS

AIRBUS DEFENCE AND SPACE ...

1. A coating method for producing a function layer on a substrate formed of a substrate material including one of a metal
sheet and a fiber composite component, the substrate deforming in response to a force in a longitudinal direction of the substrate,
and warping or twisting about the longitudinal direction in response to a torque impose on the substrate, the method comprising:
providing a first material layer made of a first material with a mechanical flexibility higher than that of a second material
at or on the substrate, such that the first material exhibits a resilient load in response to the deforming, warping and twisting
of the substrate;

structuring the first material layer so that the material layer surface of the first material layer is given a three-dimensionally
moulded basic structure with projections and recesses; and

coating the material layer surface of the first material layer with a second material layer made of the second material, such
that the second material layer adopts substantially the basic structure of the material layer surface with the projections
and recesses.

US Pat. No. 9,882,667

INTERFACE DEVICE AND METHOD FOR EXCHANGING USER DATA

Airbus Defence and Space ...

1. An interface apparatus for exchange of different time-critical user data between a host device and a divided medium, comprising:
a first interface for exchange of the different time-critical user data with the host device;
a second interface for exchange of the different time-critical user data with the divided medium;
a resource management device;
a temporary memory device;
wherein the first interface works with a first clock pulse;
wherein the second interface works with a second clock pulse, which differs from the first clock pulse;
wherein the first interface and the second interface are connected with the temporary memory device, in order to allow exchange
of the different time-critical user data between the first interface and the second interface, by way of the temporary memory
device;

wherein the resource management device is configured to control the exchange of the different time-critical user data between
the first interface and the second interface, in such a manner that collisions of the different time-critical user data within
the interface apparatus and/or on the divided medium are avoided, in order to allow deterministic behavior during the exchange
of the different time-critical user data;

wherein the resource management device is further configured to control the temporary memory device in such a manner that
the different time-critical user data is temporarily storable, using the temporary memory device, in such a manner that a
clock pulse difference between the first clock pulse and the second clock pulse is balanced out; and

wherein the resource management device is configured to control the exchange of the different time-critical user data between
the first interface and the second interface by way of management of a pointer to the first interface and/or to the second
interface.

US Pat. No. 9,879,987

POSITIONING SYSTEM AND METHOD

Airbus Defence and Space ...

1. A positioning system for detecting a spatial position of a laying head of a device for automatically laying reinforcing
fiber strips in relation to a base on which the reinforcing fiber strips can be laid by the laying head,
wherein at least two laser lines which extend substantially in parallel at a spacing from one another and substantially transversely
to a laying direction can be projected on laid reinforcing fiber strips by at least one laser source, elevation profiles of
the projected laser lines which occur on account of an irregular surface of the laid reinforcing fiber strips being able to
be recorded by a camera and supplied to an evaluation unit.

US Pat. No. 10,030,293

ALUMINUM MATERIAL HAVING IMPROVED PRECIPITATION HARDENING

Airbus Defence and Space ...

1. A method for producing an aluminum material, the method comprising the steps:a) providing an aluminum (AD-scandium (Sc)-zirconium (Zr) base alloy;
b) adding ytterbium (Yb) to the AlScZr base alloy from step a) to produce a molten aluminum (Al)-scandium(Se)-zirconium(Zr)-ytterbium (Yb) alloy;
c) cooling the molten AlScZrYb alloy obtained in step b) in a temperature interval Tliquidus to T350° C. at a cooling rate of ?100 K/sec to produce a solidified AlScZrYb alloy; and
d) heat treating the solidified AlScZrYb alloy in a temperature range from 250 to 500° C.,
wherein a weight ratio of scandium (Sc) to zirconium (Zr) to ytterbium (Yb) [Sc/Zr/Yb] is in a range from 10/5/2.5 to 10/2.5/1.25.

US Pat. No. 10,029,785

AIRCRAFT CAPABLE OF VERTICAL TAKEOFF

AIRBUS DEFENCE AND SPACE ...

1. An aircraft, comprising:a bearing structure;
the bearing structure having at least one central fuselage and two pylons, each pylon situated laterally at a distance from the fuselage;
a wing structure;
at least four hub rotors;
at least one thrust drive;
each of the hub rotors fastened to the bearing structure, having a propeller having two propeller blades, and configured to produce, through rotation of the propeller, an upward drive force acting in a vertical direction for the aircraft;
the thrust drive configured to produce a thrust force acting in a horizontal direction on the bearing structure;
each pylon having at least two hub rotors;
each hub rotor configured to arrest a respective propeller blade of a respective hub rotor in an arrested position relative to a respective pylon; and
the respective propeller blade of each hub rotor not extending, in the arrested position, beyond an outer dimension of the respective pylon,
wherein each propeller is situated in the respective pylon in such a way that each propeller is enclosed by the respective pylon on at least two opposite sides when in a non-arrested position.

US Pat. No. 9,889,945

INTAKE FOR AN ENGINE OF AN AIRCRAFT

Airbus Defence and Space ...

1. An intake for feeding air to an engine of an aircraft, comprising:
an opening for sucking in air, the opening facing a direction of movement of the aircraft; and
an air duct between the opening and the engine, wherein the air duct is curved in a way that an impact region is arranged
in the air duct after the opening in relation to the direction of movement of the aircraft, such that an object flying into
the opening contacts the impact region;

wherein the impact region has a predetermined breaking region, which is arranged in a shell-shaped part of the intake, and
wherein the predetermined breaking region protrudes from the aircraft and is designed to separate from the aircraft upon impact
of a bird as the impinging object.

US Pat. No. 9,884,682

AIRCRAFT CONFIGURATION

Airbus Defence and Space ...

1. An aircraft comprising:
a tandem wing arrangement comprising a front wing and a rear wing, and at least two aero engines disposed on the upper face
of the rear wing, wherein the aircraft has a single fuselage and wherein both wings are constructed as trapezoidal wings having
an aspect ratio (AR) in the range of 12?AR?25, in particular 16?AR?24;

wherein the at least two aero engines are disposed on pylons on the upper face of the rear wing;
wherein housing tubes are provided which extend between the front wing and the rear wing; and
wherein the housing tubes are fastened to the underside of the front wing and via the pylons connected to the upper face of
the rear wing.

US Pat. No. 10,059,425

AIRCRAFT HAVING A SELF-ERECTING PARTITION ELEMENT IN A COMPARTMENT INSIDE THE FUSELAGE

Airbus Defence and Space ...

1. An aircraft comprising:a fuselage defining a longitudinal axis of the aircraft and a compartment inside the fuselage,
wherein along the longitudinal axis, in cross-section perpendicular to the longitudinal axis, the compartment is enclosed by a floor structure and a sidewall and ceiling structure extending from and above the floor structure,
an environmental control system comprising a conduit system through which, in operation, a fluid with an overpressure with respect to the interior pressure in the compartment is supplied,
at least one first terminal spaced from the floor structure and arranged at the sidewall, disposed inside the compartment and in fluid communication with the conduit system, and
a selectively inflatable and deflatable partition element which
comprises at least one second terminal and is constructed such that it is inflatable from a deflated condition into an inflated condition by establishing a fluid communication between the at least one second terminal and at least one of the at least one first terminal,
wherein in the inflated condition, the partition element completely closes the cross-section of the compartment, such that the partition element is dividing the compartment into two portions, and in the deflated condition collapses and at least partially unblocks the cross section of the compartment,
wherein the at least one second terminal of the partition is arranged on a front side of the partition element, such that the at least one second terminal faces in longitudinal direction of the fuselage when the partition element is in the inflated condition,
wherein each of the at least one first terminal comprises a first connector and each of the at least one second terminal comprises a second connector;
wherein an interconnection tube arranged within the compartment is provided having mating connectors at the terminal ends thereof, which mating connectors are matingly connected to the first connector and the second connector, respectively, thereby establishing fluid communication,
wherein a circumferential lateral surface of the partition element is free of any terminal, and
wherein in the inflated condition, the circumferential lateral surface of the partition element is continuously and entirely in contact with the sidewall, the ceiling structure and the floor structure, respectively.

US Pat. No. 10,040,570

SENSING ORIFICE FOR AN AIRCRAFT

Airbus Defence and Space ...

1. An aircraft, comprising:a pressure port comprising
a passage through an outer skin of the aircraft; and
a moisture protection body,
wherein the passage is configured to connect with a pressure line in an interior of the aircraft,
the moisture protection body is gas-permeable and water-impermeable,
the moisture protection body is disposed so that the passage is gas-permeably and water-impermeably sealed; and
wherein the moisture protection body comprises a membrane disposed on the outer skin of the aircraft such that a coverage area over and around the passage is gas-permeably and water-impermeably sealed.

US Pat. No. 9,908,611

CHANGEABLE WING PROFILE

AIRBUS DEFENCE AND SPACE ...

1. An aerodynamic structure for a wing or rudder arrangement of an aircraft, comprising:
a support structure; and
an outer skin;
wherein the support structure comprises an adaptive surface support structure in the longitudinal direction, which extends
in the longitudinal direction from a root area to an outer end area, and is formed by a support surface, which exhibits an
adjustable periodic profiling that runs in a transverse direction, in which first and second flange areas are alternatingly
formed, and joined together by web areas running in the direction of a profile height, wherein alternatingly aligned open
profile segments running in the longitudinal direction are formed;

wherein, in the area of the open profile segments, the support structure comprises several connecting segments running in
the transverse direction, which join together two adjacent first or second flange areas;

wherein at least a portion of the connecting segments are designed as adjustable-length connecting segments, so that the distance
between the adjacent first or second flange areas can be adjusted;

wherein the width of the open profile segments can be varied by the adjustable connecting segments;
wherein the outer skin is attached to the support surface;
wherein an outer contour of the aerodynamic structure can be changed at least in the transverse direction by adjusting the
distance between the adjacent first or second flange areas;

wherein the periodic profiling comprises a repeating sequence of flanges and webs and the alternatingly aligned opened profile
segments; and

wherein the flange areas run on the two opposing outer sides of the profiling, with the first flange areas on one side and
the second flange areas on the other side.

US Pat. No. 10,137,985

STEALTH AERIAL VEHICLE

Airbus Defence and Space ...

1. A method of operating an aerial vehicle, the method comprising the acts of:taking off the aerial vehicle in a second attitude in which a first side faces down, wherein the first side of the aerial vehicle has a landing gear bay, and wherein a second side of the aerial vehicle has no bays, has a smaller radar signature than the first side and is arranged opposite to the first side of the aerial vehicle;
retracting a landing gear into the landing gear bay that is arranged on the first side;
switching from the second attitude to a first attitude in which the second side faces in a direction of a threat during a portion of flight of the aerial vehicle;
switching from the first attitude to the second attitude in which the first side faces down;
extending the landing gear while the aerial vehicle is in the second attitude; and
landing the aerial vehicle in the second attitude in which the first side faces down.

US Pat. No. 10,093,427

ULTRALIGHT AIRCRAFT

Airbus Defence and Space ...

1. An aircraft comprising:a supporting structure comprising at least one fuselage and an airfoil carrier;
a wing structure attached to the airfoil carrier;
at least one drive apparatus comprising at least one propeller and a drive motor;
at least one energy store for providing energy for operation of the drive apparatus; and
a securing device configured to mechanically connect the at least one drive apparatus and the at least one energy store to the airfoil carrier of the supporting structure,
wherein the securing device comprises at least one of a rope, a strap, a cable, a net, and a woven fabric.

US Pat. No. 10,049,590

METHOD FOR AUTONOMOUS CONTROLLING OF AN AERIAL VEHICLE AND CORRESPONDING SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. A method for autonomous controlling of an aerial vehicle, wherein a flight operator commands the aerial vehicle, comprising the steps of:measuring data of the aerial vehicle including at least flight data of the aerial vehicle;
performing an evaluation of a flight condition of the aerial vehicle based on the measured data and based on at least one decision criterion; and,
issuing at least one autonomous controlling command, if, as a result of the evaluation of the flight condition, the aerial vehicle is in danger;
wherein the at least one autonomous controlling command issued comprises at least one of:
an emergency route command that selects an emergency route, wherein the emergency route permits the aerial vehicle to land as soon as possible;
a crash route command that selects a crash route, wherein the crash route permits the aerial vehicle to go to a next reachable crash site;
an alternate route command that selects an alternate route, wherein the alternative route is prepared regarding changed air tasking orders, changed mission objectives or changed airspace coordination orders; or
an approach and landing route command that selects an approach and landing route;
wherein the evaluation of the flight condition of the aerial vehicle is performed via a traffic alert and collision avoidance system of the aerial vehicle;
wherein the measured data of the aerial vehicle includes flight data of the aerial vehicle and system data of the aerial vehicle, and
wherein data regarding at least one of:
altitude,
airspeed,
ground speed,
flight path of the aerial vehicle,
weather conditions parameters,
air temperature, or
wind speed,
is used as the flight data of the aerial vehicle for said performing an evaluation of a flight condition of the aerial vehicle;
and wherein at least one of:
health information of engines,
health information of a flight control computer, or
health information of further units of the aerial vehicle,
is used as the system data of the aerial vehicle for said performing an evaluation of a flight condition of the aerial vehicle.

US Pat. No. 9,998,035

RESONANT ENERGY HARVESTER, AIRCRAFT COMPONENT COMPRISING THE RESONANT ENERGY HARVESTER AND AN AIRCRAFT COMPRISING THE RESONANT ENERGY HARVESTER OR THE AIRCRAFT COMPONENT

AIRBUS DEFENCE AND SPACE ...

1. An energy harvester for an aircraft, comprising:a first portion including a charge collecting device having an electrical permittivity different to that of air, the charge collecting device being configured to be exposed to an air flow;
a movable element configured to be driven by a charge of the charge collecting device, the movable element comprising an elastic element having a fixed first end and a second end, the elastic element comprising a conductive material, and the second end being arranged to move freely and disposed in the vicinity of the first portion, and a second portion configured to be exposed to an air flow, the second portion comprising a conductive material and being electrically connected to the first end; and
a kinetic-to-electric-energy-converter configured to generate energy by movement of the movable element, the kinetic-to-electric-energy-converter being fixed to the elastic element.

US Pat. No. 9,989,378

DISPLAY OF AIRCRAFT ALTITUDE

Airbus Defence and Space ...

1. A method of operating an attitude indicator unit of an aircraft so as to display an attitude of the aircraft, the method comprising the steps of:receiving at a processor a roll angle, a pitch angle and a yaw angle of the aircraft;
generating via the processor a display image indicating the roll angle, the pitch angle and the yaw angle;
displaying the display image on a display device, wherein the display image is a virtual object that comprises:
a spherical shell with a track angle scale projected onto the spherical shell along a latitude line of the spherical shell and with a pitch angle scale projected onto the spherical shell along a longitude line of the spherical shell, the track angle scale and the pitch angle scale defining coordinates on the spherical shell, and
a graphical aircraft attitude indicator inside the spherical shell and rotated with respect to the spherical shell according to a viewing perspective such that the graphical aircraft attitude indicator indicates the roll angle, the pitch angle and the yaw angle of the aircraft with respect to the spherical shell, wherein the graphical aircraft attitude indicator comprises a graphical pitch angle indicator that identifies a coordinate on the spherical shell, the coordinate corresponding to the pitch angle and the track angle according to the pitch angle scale and the track angle scale; and
rotating via the processor the spherical shell so as to adjust the viewing perspective while maintaining the identification of the coordinate on the spherical shell by the graphical pitch angle indicator.
US Pat. No. 9,937,692

METHOD FOR THE MANUFACTURE OF REINFORCED MATERIALS AND MATERIAL THAT CAN BE OBTAINED FROM THIS METHOD

AIRBUS DEFENCE AND SPACE ...

1. A method for the manufacture of making reinforced core composites, the method comprising:inserting a pin into a foamed core material or a filled honeycomb-shaped core material, wherein the pin and the core material contain a thermoplastic polymer, or a mixture of thermoplastic polymers;
and at least one of
heating the pin such that as the pin is inserted the core material softens or melts at the point of insertion; and
heating the core material at the point of insertion such that the core material softens or melts,
wherein the core material is reinforced with particles that are located within the core material.

US Pat. No. 9,919,786

ACOUSTIC CABIN PANEL

AIRBUS DEFENCE AND SPACE ...

1. An acoustical cabin panel, comprising:
a first and a second layer which are spaced apart from each other by an intermediate layer and altogether with a plurality
of reinforcement elements form a core composite component;

at least one intermediate sublayer made of a core material that is placed in the intermediate layer;
wherein the reinforcement elements extend from the first to the second layer through the at least one intermediate sublayer
and are tension and pressure resilient in a finished state of the panel;

wherein the reinforcement elements can be at least partially infiltrated with a curable matrix material;
wherein at least one prepreg soaked with matrix material is provided in the first and/or second layer;
wherein the reinforcement elements to be infiltrated with matrix material are in connection with the prepreg; and
wherein the core material is a silicone foam rubber.

US Pat. No. 10,110,297

AIRCRAFT COMPRISING A PLURALITY OF ANTENNA UNITS

AIRBUS DEFENCE AND SPACE ...

1. An aircraft comprising:at least two antenna units and
a central control unit, wherein,
in a first mode of operation, the at least two antenna units are configured to transmit and/or receive signals, independently of one another, that are in different, non-overlapping frequency bands, and,
in a second mode of operation, the central control unit is configured to control the at least two antenna units such that said antenna units transmit and/or receive a common signal in a common frequency band by means of multiple-input multiple-output transmission technology, wherein the central control unit is set up to control the at least two antenna units in a manner corresponding to the second mode of operation when the aircraft is on the ground, wherein the at least two antenna units are set up to transmit and/or receive signals in a manner corresponding to the first mode of operation when the aircraft is in the air, and wherein the central control unit automatically detects when the aircraft has landed and switches the mode of operation.

US Pat. No. 9,970,814

METHOD FOR PROCESSING ITEMS AND DEVICE AND USE THEREOF

Airbus Defence and Space ...

1. A method for processing items, the method comprising:measuring at least one item using a partial quantity of sensors associated with at least one sensor arrangement having a plurality of sensors;
determining, by a control means, the impacting of the at least one item with an irradiation means while considering a result of the measuring procedure of the at least one item; and
irradiating the at least one item by at least a further partial quantity of the plurality of sensors as the irradiation means in an irradiation mode; and
if appropriate, repeating at least part of the method.

US Pat. No. 9,950,781

EFFECTOR WITH EJECTABLE STEALTH SHELL

Airbus Defence and Space ...

1. An effector for an aircraft, the effector comprising:an effector body; and
a stealth shell enclosing the effector body at least in part,
wherein the stealth shell is attached to the effector body,
wherein the stealth shell is configured so as to be separated from the aircraft and from the effector body during flight of the aircraft carrying the effector,
wherein the effector body comprises a plurality of wing-like extensions,
wherein the stealth shell has a plurality of shell elements each arranged between two of the plurality of wing-like extensions and comprising recesses or indentations on each lateral edge of each respective shell element, such that the plurality of wing-like extensions are receivable between two adjacent ones of the plurality of shell elements, and
wherein each of the shell elements has an angled outer contour on a side facing away from the effector body such that the stealth shell has a circumferential edge running around a direction of longitudinal extension of the entire effector body, thereby reducing a radar backscatter cross-section of the effector.

US Pat. No. 9,928,984

GAS INLET FOR AN ION THRUSTER

Airbus Defence and Space ...

1. A gas inlet for use in an ion thruster, comprising:a housing made of a gas-tight ceramics material; and
an insert which is arranged in the housing and made of a porous ceramics material, wherein a geometry and pore structure of the insert are configured such that the insert forms a desired flow resistance for a gas stream flowing through the insert.

US Pat. No. 9,927,513

METHOD FOR DETERMINING THE GEOGRAPHIC COORDINATES OF PIXELS IN SAR IMAGES

Airbus Defence and Space ...

1. A method, comprising:determining, by a processor of an airborne device, geographic coordinates of corresponding pixels of a target from first and second digital synthetic aperture radar (SAR) images by
capturing, by the processor of the airborne device, the first and second SAR images in a form of slant range images;
determining, by the processor of the airborne device, a recording position of the respective first and second SAR images;
determining, by the processor of the airborne device, a distance between a corresponding resolution cell on a ground and the respective recording position of the respective first and second SAR images using coordinates of the corresponding pixels of the target in the first and second SAR images and corresponding range gates; and
determining, by the processor of the airborne device using the determined distances and associated recording positions of the first and second SAR images, the geographic coordinates of the corresponding pixels of the target in the first and second SAR images by
producing, by the processor of the airborne device, a first and second sphere for the first and second SAR images using the determined distances and associated recording positions of the first and second SAR images; and
determining, by the processor of the airborne device, the geographic coordinates of the corresponding pixels of the target as a common intersection of the first and second spheres with the WGS84 ellipsoid.

US Pat. No. 9,916,650

IN-PROCESS FAULT INSPECTION USING AUGMENTED REALITY

Airbus Defence and Space ...

1. An arrangement for visual fault inspection of at least one component, comprising:
a fault identification unit configured to identify a structural fault in the component and to determine at least one item
of fault information;

an overlay device connected to the fault identification unit and configured to overlay the at least one item of fault information
in a context-dependent manner in a component image in real-time,

a positioning-finding unit configured to determine exact positioning information about a position of the component and about
a position of the user;

a processor unit connected to the fault identification unit and to the position-finding unit, the processor unit being configured
to process the at least one item of fault information and the positioning information and to integrate the processed information
in the component image; and

a visualisation unit connected to the processor unit configured to display the component image containing the integrated information
of the processor unit.

US Pat. No. 9,897,041

ENGINE FOR PROPELLING AN AIRCRAFT AND AIRCRAFT HAVING AT LEAST ONE ENGINE AND AT LEAST ONE HYDROGEN TANK

Airbus Operations GmbH, ...

1. An engine for propelling an aircraft, comprising:
a fuel cell arrangement having at least one fuel cell unit;
at least one electric motor couplable to the fuel cell arrangement;
at least one first fan couplable to the at least one electric motor; and
an outermost cowling having an inlet and an outlet nozzle,
wherein the fuel cell arrangement is positioned at an inner surface of the outermost cowling, said inner surface of the outermost
cowling defining a flow duct of the at least one first fan,

said fuel cell arrangement configured to receive a portion of an airflow generated by the at least one first fan in said flow
duct,

wherein the at least one first fan is arranged between the inlet and the fuel cell arrangement inside the outermost cowling,
wherein the at least one electric motor is operable under consumption of electric power delivered by the fuel cell arrangement,
and

wherein the at least one first fan is configured to produce a thrust force by creating an accelerated airflow at the outlet
nozzle.

US Pat. No. 10,150,557

SHAPE-VARIABLE GAP COVERING BETWEEN CONTROL SURFACES AND ADJACENT STRUCTURAL COMPONENTS ON AIRCRAFTS

Airbus Defence and Space ...

1. A transition piece for forming a continuous surface from a structural component of an aircraft to a control surface, wherein the control surface has a front edge, a rear edge and two lateral edges, wherein the front edge or the rear edge of the control surface is pivotally connected to the structural component,wherein the transition piece is configured to be mounted in a recess formed between an edge of the structural component and one of the lateral edges of the control surface,
wherein the transition piece is configured to be pivotally mounted on the edge of the structural component and to be pivotally mounted on the lateral edge of the control surface, and
wherein the transition piece is planar flat and extends in a plane and is configured to be deformed within the plane.

US Pat. No. 10,018,210

COMPONENT HAVING AN INTEGRAL BOND AND JOINING METHOD

Airbus Defence and Space ...

1. A component comprising:at least first and second plastics component parts interconnected in a connection zone such that the first and second plastics component parts overlap in the connection zone; and
a reinforcing element comprising at least one wire extending through the connection zone and embedded at least partially in the first and second plastics component parts in the connection zone,
wherein the at least one wire comprises a plurality of connected helical wires interwoven in the form of a mat, and
wherein the at least one wire on surfaces of the first and second plastics component parts opposite the connection zone does not protrude beyond said first and second plastics component parts and/or is not visible on said surfaces.
US Pat. No. 9,941,540

COMPOSITE ELECTROLYTE FOR A SOLID OXIDE FUEL CELL, EXHAUST GAS PROBE OR HIGH-TEMPERATURE GAS SENSOR

AIRBUS DEFENCE AND SPACE ...

1. A sinterable composite electrolyte compound comprising:a) an electrolyte selected from the group consisting of 8YSZ, 10Sc1CeSZ, 10Sc1AlSZ, 10Sc2YbSZ, 3YSZ, 6ScSZ and mixtures thereof, and
b) a material distributed in the electrolyte in a quantity from 0.1 to 15.0% by weight relative to the total weight of the electrolyte, wherein the material has an average particle size d50 from 1 to 80 nm and comprises at least two materials selected from the group consisting of 8YSZ, Al2O3, MgO, Al, Mg, 3YSZ, 6ScSZ, 10Sc1CeSZ, 10Sc1AlSZ, 10Sc2YbSZ and mixtures thereof.

US Pat. No. 10,040,906

CYANATE ESTER/ARYL ETHYNYL POLYIMIDE RESINS FOR COMPOSITE MATERIALS

Airbus Defence and Space ...

1. A polymerizable thermoset composition comprising:a) a cross-linkable organic cyanate ester resin;
b) a cross-linkable aryl ethynyl-terminated polyimide, and
c) at least one allyl compatibilizer comprising at least two functional groups, wherein the functional groups are each independently selected from the group consisting of hydroxides, primary amines, secondary amines, anhydrides, cyanate esters, and epoxides.

US Pat. No. 10,183,356

WELDING TOOL COMPRISING A SHOULDER, WELDING METHOD AND WORKPIECE

Airbus Defence and Space ...

1. A welding method for connecting at least two workpieces at a connection region by means of friction stir welding using a welding tool having a probe and a shoulder, the method comprising:rotating the probe around a rotation axis, wherein the connection region is softened by friction heat provided by the probe during said friction stir welding to form a welded seam at the connection region;
molding, simultaneously with forming the welded seam, at least one of a bevel, a rounding and a chamfer on an edge of the connection region using the shoulder, wherein the shoulder is configured to separate the connection region from the surroundings, and
molding an inner corner of the at least two workpieces onto an inner clamp block.

US Pat. No. 10,104,206

NETWORK MODULE FOR SENDING AND/OR RECEIVING OF DATA PACKAGES FROM A NETWORK ARRANGEMENT AND METHOD

Airbus Defence and Space ...

1. A network module for sending and/or receiving of data packages from a network arrangement provided in a network with a ring structure, wherein each of the data packages comprises at least one data package segment, a source address, a destination address and an identification number, the network module comprising:a first network interface for receiving and/or sending of data packages via the ring structure;
a second network interface for receiving and/or sending of data packages via the ring structure;
a processor configured to determine, based on the destination address, if data packages received with the first network interface and/or the second network interface are directed to the network module and to determine if the source address and/or the destination address are contained in a predefined list of network participants,
wherein the processor is further configured to determine, based on the source address and the identification number, if a copy of a data package directed to the network module is already created in a memory,
wherein the processor is further configured to create a copy of the data package as well as the source address and the identification number in the memory if the determination results in that the received data package is directed to the network module and a copy of the data package has not yet been created in the memory, and
wherein the processor is further configured to unpack the data package segment comprising at least one header and a payload from the created copy of the data package and to provide the data package segment to an application.

US Pat. No. 10,016,821

DEVICE FOR MACHINING EDGES

Airbus Defence and Space ...

1. A device for machining workpieces, comprisinga machining tool;
a first workpiece-guiding element;
a second workpiece-guiding element, and
a hollow drive shaft for driving the machining tool, the hollow drive shaft being rotatable around the first workpiece-guiding element,
wherein the first workpiece-guiding element and the second workpiece-guiding element are configured to guide a workpiece relative to the machining tool in a defined manner,
wherein the machining tool has a rotational axis and a coaxial opening,
wherein the machining tool rotates about the rotational axis for workpiece machining,
wherein the first workpiece-guiding element is arranged in the opening in the machining tool so as to be coaxial with the rotational axis,
wherein the first workpiece-guiding element is a pin shaped element extending completely through the hollow drive shaft,
wherein the first workpiece-guiding element is static,
wherein the second workpiece-guiding element is a planar element in the form of a work table having a support surface.

US Pat. No. 9,975,636

CARGO RESTRAINING ASSEMBLY, CARGO LOADING SYSTEM AND AIRCRAFT

Airbus Defence and Space ...

1. A cargo restraining assembly configured to be mounted to a cargo deck surface of an aircraft, the cargo restraining assembly comprising:two guidance and restraint bars oriented parallel to each other; and
at least one lateral bracket spanning between the two guidance and restraint bars, wherein the at least one lateral bracket is fixedly connected to each of the two guidance and restraint bars,
wherein the at least one lateral bracket comprises a bracket foot formed integrally therewith and a quick release mechanism to couple the bracket foot to a seat track profile of the cargo deck surface of the aircraft in a manner that is quickly releasable,
wherein the two guidance and restraint bars include respective angled restraining flanges that are oriented outwards, away from the at least one lateral bracket, the angled restraining flanges comprising a flange portion for preventing movement of adjacent cargo items in a z-direction, which is normal to a plane of extension of the cargo deck surface, and
wherein the at least one lateral bracket is fixedly connected to each respective angled restraining flange.
US Pat. No. 10,550,232

THIN FILM BARRIER COATING FOR CFRP

University of Surrey, Su...

1. An article comprising:(i) a carbon fibre reinforced plastic (CFRP) substrate, wherein the CFRP substrate comprises a resin matrix system with a reinforcement comprising carbon fibres, aligned with each other in substantially one direction, disposed therein, wherein the reinforcement does not comprise a particulate dispersion,
(ii) a buffer layer disposed adjacent the CFRP substrate, and comprising a poly(para-xylylene) polymer; and
(iii) a moisture barrier coating comprising diamond-like carbon disposed adjacent the buffer layer.

US Pat. No. 10,131,426

AIRCRAFT CAPABLE OF VERTICAL TAKE-OFF

Airbus Defence and Space ...

1. An aircraft, comprising:a support structure;
a wing structure;
at least three lifting rotors; and
at least one thrust drive;
wherein the wing structure is attached to the support structure or is part of the support structure,
wherein the wing structure is configured to generate a lifting force for the aircraft during horizontal motion of the aircraft using at least one aerofoil which is provided with a profile generating a dynamic lift,
wherein each of the at least three lifting rotors is attached to the support structure, has a propeller and is configured to rotate the propeller to generate a lifting force, acting in the vertical direction, for the aircraft,
wherein the propeller of each of the at least three lifting rotors has exactly two propeller blades,
wherein the at least one thrust drive is configured to generate a thrust force, acting in the horizontal direction, on the support structure, and
wherein the at least one thrust drive generates a horizontally-acting thrust such that the aircraft is accelerated to a high cruising speed independently of the lifting rotors after the lifting rotors have stopped.

US Pat. No. 10,127,678

MODULAR DEVICE FOR HIGH-SPEED VIDEO VIBRATION ANALYSIS

AIRBUS DEFENCE AND SPACE ...

1. A device for high-speed video vibration analysis, the device comprising:a camera arrangement configured to generate at least two high-speed video streams of the structure;
a data analyzer unit, connected to the camera arrangement, the data analyzer unit comprising
a processing unit configured to:
estimate, from at least one of the at least two high-speed video streams, deformations of at least a portion of the captured structure along a first plane,
determine, from the at least two high-speed video streams, depth information of at least a portion of the captured structure being one of along a second plane, different from the first plane, or along an axis included in the second plane,
detect vibration modes associated with the estimated deformations of at least the portion of the captured structure along the first plane, and
extract vibrational data of at least a portion of the captured structure by combining the estimated deformations of at least the portion of the captured structure along the first plane, the detected vibration modes associated with the estimated deformations of at least the portion of the captured structure along the first plane and the determined depth information of at least the portion of the captured structure along the second plane.

US Pat. No. 10,511,588

FORWARD-SECURE CRASH-RESILIENT LOGGING DEVICE

Airbus Defence and Space ...

1. A method of verifying integrity of log entries stored in log entry locations of a storage device, the method comprising:replaying a pseudorandom generator used to determine log entry locations for storing log entries to determine a log entry location in which a particular log entry is to be stored after a predetermined number of log entries has been stored using a method comprising:
encrypting a log message using a secret to create an encrypted log message;
calculating an authentication code from the secret and the encrypted log message to create a log entry comprising the encrypted log message and the authentication code; and
determining a random one of the log entry locations to become a selected log entry location for storing the log entry;
wherein the selected log entry location is determined by using a pseudo random function,
wherein the log entry locations are organized as a numbered sequence, in that only as many log entry locations are used as there are log entries and dummy log entries to be stored and in that an unbroken sequence of log entry locations is used to store the log entries and the dummy log entries, and
verifying integrity of the log entry stored in the log entry location previously determined by verifying the authentication code stored together with the encrypted log message.

US Pat. No. 10,287,719

APPARATUS AND METHOD FOR PROVIDING REINFORCEMENT STRAND LOOPS

Airbus Defence and Space ...

1. A device for providing reinforcement strand loops for a multi-needle system for mechanically reinforcing a component made of a foamed plastics material, the device comprising:a profile body;
at least two clamps positioned on a periphery and/or an end face of the profile body for fixing a reinforcement strand to the profile body;
at least one slider that is movable in parallel with a central longitudinal axis of the profile body to form the reinforcement strand loops;
at least two separators positioned in the periphery and/or the end face of the profile body for separating the reinforcement strand loops from the reinforcement strand; and
a feeder for feeding the reinforcement strand to the profile body.

US Pat. No. 10,252,476

REPEATING UNIT, MULTI-NEEDLE MACHINE AND METHOD FOR PRODUCING REINFORCED MATERIALS

Airbus Defence and Space ...

1. A repeating unit for a feed device of a multi-needle machine that initially positions a semi-finished textile product along a straight path, the repeating unit comprising:a first device;
a slider mounted on the first device;
a second device;
at least one pin mounted on the second device, wherein at least one of the first and second devices is rotatably supported about an axis;
a linear guide which passes through the first device and the second device parallel to the axis; and
a carriage that feeds the semi-finished textile product between the slider and the at least one pin;
wherein a rotation of the at least one of the first and second devices causes movement of the pin along a circular path and past the slider, and/or causes movement of the slider along a circular path and past the pin, to facilitate engagement of the semi-finished textile product with the slider and the at least one pin, and to facilitate displacement and arrangement of the semi-finished textile product along a cyclical, non-straight path in an area of a rear surface of a material to be reinforced.

US Pat. No. 10,184,460

CUSPED-FIELD THRUSTER

Airbus Defence and Space ...

1. A cusped-field thruster for a space system, wherein the cusped-field thruster comprises:at least two substantially annular permanent magnets arranged in an antipolar manner, wherein a magnetic pole piece is formed between the at least two substantially annular permanent magnets; and
an anode, which comprises another permanent magnet, wherein the anode has a continuously tapering profile;
wherein the cusped-field thruster is configured in such a way that a cusp of a magnetic field is formed in a region adjacent to the anode of the cusped-field thruster.

US Pat. No. 10,183,446

COMPONENT HAVING AN INTEGRAL BOND AND A JOINING METHOD

Airbus Defence and Space ...

1. A welding method for producing an integral bond of a first and a second plastics part in a connection region, the method comprising:reinforcing at least the first plastics part by a plurality of directional fibres;
providing an overlap region in which the first plastics and the second plastics part overlap;
bringing a welding head being into contact with the first plastics part in the overlap region;
softening and/or melting the plastics material in the connection region adjacent to one end of the first plastics part so that the welding head can penetrate the first plastics part and the reinforcing fibres can extend from said end into the connection region by appropriate heating.

US Pat. No. 10,179,651

SEAT FASTENING DEVICE

Airbus Defence and Space ...

1. A seat fastening device for fastening vehicle seats in a vehicle, comprising:a seat track and
a slider in a sliding engagement with the seat track,
the slider including a seat fixation element configured to fix a vehicle seat,
the seat track including a C-shaped profile,
the slider including a base inserted in the C-shaped profile, and
the slider including a clamp configured to clamp the slider against an inner surface of the C-shaped profile, and
at least one linear roller contact bearing comprising a ball race configured to receive a ball bearing between the C-shaped profile and the slider.

US Pat. No. 10,166,729

DEVICE FOR CONSOLIDATING A PREFORM

Airbus Defence and Space ...

1. A device for consolidating a thermoplastic preform, comprising:a heating element for heating the preform; and
a consolidation element for exposing the preform to pressure and for cooling the preform,
wherein, to consolidate the preform, the heating element and consolidation element are arranged and are movable relative to each other in such a way that the preform is exposed to pressure and cooled by the consolidation element after being heated by the heating element,
wherein the consolidation element comprises at least two adjacent consolidation rollers,
wherein the heating element and the consolidation rollers are configured and arranged to be moved along the preform in such a way that the preform is heated region by region by the heating element, and subsequently pressurized and cooled by the consolidation rollers,
wherein the consolidation rollers are configured and arranged to be guided along the preform by a web guide,
wherein the web guide comprises a guide groove and a guide arm, at least one of the heating element and the two consolidation rollers being arranged on the guide arm,
wherein a shape of the guide groove corresponds to a shape of the preform and enables guiding the consolidation rollers along the shape of the preform,
wherein the guide arm comprises a connecting part having a first longitudinal end and a second longitudinal end opposing the first longitudinal end, the heating element and the two consolidation rollers being attached to the first and second longitudinal ends, respectively, thereby being spaced apart from each other,
wherein the guide arm further comprises a guide part joined to the connecting part at a right angle to form a single part, and the consolidation rollers are mounted at a first longitudinal end of the guide part facing the connecting part,
wherein the guide part is, at a second longitudinal end facing away from the connecting part, hinged in the guide groove, and
wherein the heating element is pivotably secured to the connecting part so that the heating element can pivot around a longitudinal axis of the heating element, so that the preform is radiated at various angles, and can thus be heated at varying intensities.

US Pat. No. 10,343,373

COATED COMPOSITE COMPONENT

Airbus Defence and Space ...

1. A coated composite component comprising,an uncured composite component;
a fluorine-containing film and/or a fluorine-containing fabric disposed on the composite component; and
a tear-off fabric disposed on the composite component and covering all edges of the fluorine-containing film and/or fabric;
wherein a surface area of the fluorine containing film and/or fabric is smaller than a surface area of the tear-off fabric and smaller than a surface area of the composite component, and
wherein the tear-off fabric only partially covers the surface area of the fluorine-containing film and/or fabric.

US Pat. No. 10,312,392

MULTI-JUNCTION SOLAR CELL FOR SPACE APPLICATIONS

Airbus Defence and Space ...

1. A multi junction solar cell, comprising:a first main surface and a second main surface opposite to the first main surface of a semiconductor body, wherein a topmost pn-junction of a plurality of pn-junctions stacked on top of each other adjoins to the first main surface;
a cell edge of the semiconductor body defining a shape of the first and the second main surfaces;
an encapsulant arranged on the first main surface to protect the semiconductor body from an environment;
a mesa groove arranged on the first main surface, wherein the mesa groove is filled with the encapsulant, and
a coverglass is located on the encapsulant to seal the solar cell and the mesa groove on the first main surface,
wherein the mesa groove is located adjacent to the cell edge to provide an inner cell area and a mesa wall,
wherein a conductive or antistatic material that provides an electrical shunt path is applied on the cell edge which extends between a back side of the solar cell and a front side of the solar cell, the back side being provided by the second main surface and the front side being provided by the coverglass, thereby at least directly contacting the coverglass, the encapsulant, and the mesa wall.

US Pat. No. 10,286,613

LAYERED CONSTRUCTION OF A FIBROUS BODY

Airbus Defence and Space ...

14. A method for producing a fibrous body, comprising:constructing the fibrous body in layers by alternately applying a fiber-matrix material to a layer substrate; and
fusing each applied layer of the fiber-matrix material to the layer substrate,
wherein the fibrous body comprises a plurality of crosslinked structures and wherein the fiber-matrix material contains a matrix material and a plurality of short fibers and/or fiber particles, and wherein the layer substrate comprises an electrically conductive material, and
wherein fusing comprises connecting at least part of the layer substrate to a current source.

US Pat. No. 10,263,611

DC SWITCHING DEVICE AND METHOD OF CONTROL

Airbus Defence and Space ...

1. A DC switching device comprising:at least one switching unit arranged between two terminals; and
at least one control unit for controlling the switching unit, wherein the at least one control unit comprises at least one switch;
the switching unit comprising at least a first and a second semiconductor switching element, which are arranged in parallel with one another, the first switching element being a high-voltage switching element and the second switching element being a low-power-loss switching element,
wherein the switching unit is controllable by the control unit such that:
when the switching unit is switched off, initially the second switching element is switched to be non-conductive, and subsequently the first switching unit is switched to be non-conductive; and
when the switching unit is switched on, initially the first switching element is switched to be conductive, and subsequently the second switching element is switched to be conductive.

US Pat. No. 10,207,811

CARRIER SYSTEM FOR CARRYING OUT INTERCEPTION MANEUVERS OF A LOADBEARING PARAGLIDER AND METHOD FOR ADJUSTING THE TRAILING EDGE OF A LOADBEARING PARAGLIDER

Airbus Defence and Space ...

1. A loadbearing paraglider, comprising:a glider having a trailing edge for carrying out a manoeuvre;
a carrier system connected to the glider by a plurality of lines;
at least one carried load unit connected to the carrier system via a first, short load carrier belt and a second, longer load carrier belt;
a carried load connected to the carried load unit;
wherein the carried load unit is carried by way of the first, short load carrier belt, wherein at least one interception line is fixed to the at least one carried load unit and the trailing edge; and
wherein the trailing edge is adjusted to carry out the maneuver by the gravitational force of the carried load, in that the first, short load carrier belt is separated so as to no longer connect the carried load unit to the carrier system and the carried load unit is subsequently carried by way of the longer, second load carrier belt and the interception line.
US Pat. No. 10,150,277

CONNECTION ELEMENT, CONNECTION ARRANGEMENT, METHOD FOR PRODUCING A CONNECTION ELEMENT AND METHOD FOR PRODUCING A CONNECTION ARRANGEMENT

Airbus Defence and Space ...

1. A connection element comprising:a composite component comprising a cured epoxy resin;
a first layer comprising a first thermoplastic polymer;
an intermediate layer arranged between the composite component and the first layer and containing both the epoxy resin of the composite component and the first thermoplastic polymer of the first layer;
wherein the first thermoplastic polymer has a melting point, in particular a glass transition temperature, above a curing temperature of the epoxy resin;
wherein the first thermoplastic polymer is soluble at a temperature of at least 150° C. in the epoxy resin used for producing the composite component;
wherein the curing temperature of the epoxy resin is up to 180° C.;
wherein the glass transition temperature of the first thermoplastic polymer is higher than 185° C., in particular higher than 200° C.; and
wherein the epoxy resin extends into the intermediate layer, from the composite component towards the first layer, in a form of a number of volume portions which are mutually adjacent or interconnected at least in part, wherein the volume portions are configured as bubbles and have, in a region of the intermediate layer that is adjacent to the composite component, a diameter or a volume that is greater than in a region of the intermediate layer that is adjacent to the first layer.

US Pat. No. 10,120,771

MULTIUSE-CAPABLE TEST ENVIRONMENT FOR A PLURALITY OF TEST OBJECTS

Airbus Defence and Space ...

1. An arrangement for providing a test environment for testing test objects, comprising:a first test case implementation unit and a second test case implementation unit;
a plurality of test objects, including a first test object and a second test object, each of which comprises an aircraft computer,
wherein the test environment is configured such that at least the first test case implementation unit is coupled to at least one of the first test object and the second test object for implementing a test case;
a connection unit that is configured to selectively couple one of the first test case implementation unit and the second test case implementation unit to at least one of the first test object and the second test object; and
a plurality of mechanical simulation hardware units that are actuated by the plurality of test objects during a test case,
wherein each of the plurality of simulation hardware units may be selectively coupled to one of the plurality of test objects via the connection unit,
wherein the plurality of simulation hardware units are arranged spatially separated from the plurality of test objects.

US Pat. No. 10,081,443

AIRCRAFT INSPECTION SYSTEM

Airbus Defence and Space ...

12. An aircraft comprising:an operating system for operating the aircraft; and
an aircraft inspection system comprising:
at least one movable inspection unit;
a position detection arrangement; and
at least one data transfer interface;
wherein the at least one movable inspection unit:
is configured as an unmanned vehicle unit which is movable in relation to an aircraft to be inspected during a predetermined operation phase of the aircraft, when the aircraft is not in parking position;
comprises at least one sensor for: detecting a characteristic value, verifying a characteristic, and/or determining a defect of an aircraft; and
is configured to generate monitoring data;
wherein the position detection arrangement is configured to detect position data of the movable inspection unit in relation to the aircraft to be inspected upon detection of the characteristic value, the verified feature, or the determined defect, and to assign the position data to the monitoring data;
wherein the data transfer interface is configured to provide the position data with the assigned monitoring data in the form of inspection data, and
wherein the inspection data are taken into account for operating the aircraft.

US Pat. No. 10,059,089

METAL OR CERAMIC COMPONENT COMPRISING AT LEAST ONE MULTI-DIMENSIONALLY STRUCTURED CONNECTION PORTION AND METHOD FOR THE PRODUCTION THEREOF

Airbus Defence and Space ...

1. A method for multi-dimensionally structuring at least one connection portion of a metal component, wherein the connection portion is intended for forming an adhesive bond to fiber-reinforced polymer laminate, and wherein the method comprises:producing a milliscale structure by forming anchoring elements on the connection portion which protrude from the connection portion substantially perpendicularly or at a predetermined angle by stamping-and-bending processes, high-speed metal machining, electron beam machining, additive layer production processes, deposit welding or welding on of anchoring elements;
producing a microscale structure on the connection portion and the anchoring elements by sandblasting or electromagnetic radiation;
producing a nanoscale structure over the microscale structure on the connection portion and the anchoring elements.

US Pat. No. 10,272,989

HIGH-LIFT SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. A high lift system for an aircraft, comprising:a wing;
a carriage coupled to the wing;
a high lift flap arranged on the wing and mounted to the carriage;
a track on which the carriage is displaceably mounted; and
a high lift bearing for mounting the track;
wherein the high lift bearing comprises a plurality of slide blocks in sliding contact with surfaces of the track;
wherein the slide blocks are trapezoidal, an angle on a side facing the track being an acute angle;
wherein the track comprises opposing flanges comprising a first flange and a second flange;
wherein the carriage comprises:
a joint, coupled to the high lift flap, and having a point of rotation;
a guide shoe overlying and flanking the flanges, and the guide shoe comprising four ends extending away from the joint; and
retaining structures arranged at opposite sides of the track, each retaining structure coupled to a respective one of the four ends of the guide shoe, and each retaining structure comprising two slide blocks arranged to be in sliding contact with surfaces of the track to accommodate movement of the carriage along the track;
wherein the two slide blocks of each retaining structure include a first slide block located to slide on an underside of a respective one of the flanges, and a second slide block located to slide on a lateral surface of the respective one of the flanges.

US Pat. No. 10,243,649

NEAR-REAL TIME EIRP MONITORING DEVICE/SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. A method for detection of an Equivalent Isotropically Radiated Power (EIRP) degradation of a radio frequency (RF) transmitter of a satellite being in an orbit with a repeating ground track, the method comprising:obtaining sets of signal-to-noise (C/N0) data from a first source and obtaining satellite orbit data of the satellite from a second source, wherein each set of C/N0 data is associated with the satellite and a respective one of a plurality of receivers;
computing temporal information on an elevational and azimuthal direction of the satellite with respect to respective locations of each of the plurality of receivers based on the satellite orbit data and the respective locations of each of the plurality of receivers;
determining a time interval based on the temporal information, in which time interval the repeating ground track repeats a single time;
determining, for each of the plurality of receivers, a respective one of a first plurality of differences between a first value of the respective set of C/N0 data corresponding to a first time point and a second value of the respective set of C/N0 data corresponding to a second time point, wherein the first and second time points are apart by the time interval;
computing a first average of the first plurality of differences;
comparing the computed first average with a predetermined threshold; and
triggering a signal, which indicates detection of the EIRP degradation of the transmitter when the computed first average is larger than the predetermined threshold.

US Pat. No. 10,207,790

CHANGEABLE WING PROFILE

AIRBUS DEFENCE AND SPACE ...

1. An aerodynamic structure for a wing or rudder arrangement of an aircraft, comprising:a support structure; and
an outer skin;
wherein the support structure comprises a fixed spar in the longitudinal direction, which extends from a root area to an outer end area;
wherein the support structure comprises several adaptive framework segments in the transverse direction, each comprising a plurality of strung together triangular compartments that are formed by fixed-length guide elements and adjustable-length guide elements;
wherein the framework segments are joined to the fixed spar;
wherein at least one side of at least a portion of the triangular compartments comprises one of the adjustable-length guide elements, so that the shape of the framework segments can be adjusted;
wherein the outer skin is held by the framework segments;
wherein an outer contour of the aerodynamic structure can be changed at least in the transverse direction by adjusting the shape of the framework segments;
wherein the adjustable-length guide elements are active actuating drives; and
wherein the adjustable-length guide elements in the triangular compartments are arranged such that each triangular compartment comprises an adjustable-length guide element facing the outside, wherein the triangular compartments are arranged such that adjustable-length guide elements are provided on alternating upper and lower sides of the aerodynamic structure.

US Pat. No. 10,150,263

TESTING ARRANGEMENT FOR CONTROLLING THE MANUFACTURING OF A COMPONENT

Airbus Defence and Space ...

1. A testing arrangement for controlling a manufacturing of a fiber reinforced component, wherein the testing arrangement comprises:an inspection device with a sensor system, the inspection device being configured to move on and/or above one or more material layer(s) and/or a surface of the component and to examine the material layer(s) or the surface with the sensor system,
wherein the inspection device is configured to move in a forming tool dissociated or separated from a laying head which lays the material layers in an automated layer laying process, and
wherein the inspection device is configured to change its direction of movement relative to a direction of movement of the laying head, and
wherein the inspection device comprises at least one actuator for removing a defect.

US Pat. No. 10,144,200

FIBER-REINFORCED COMPOSITE MATERIAL WITH IMPROVED FIRE RESISTANCE, AND STRUCTURAL COMPONENT MADE THEREOF

Airbus Defence and Space ...

1. A fiber-reinforced composite material, comprising:a multilayer bulk portion forming a bulk of the fiber-reinforced composite material and comprising a plurality of fiber material layers embedded in a bulk matrix; and
a surface portion comprising a plurality of laminated first layers structurally configured to expand or delaminate during fire impact and a plurality of laminated second layers different from the plurality of laminated first layers, wherein the plurality of laminated first layers are arranged in an alternating sequence with the plurality of laminated second layers,
wherein at least one of the laminated first layers comprises a thermoplastic film, the thermoplastic being a polymer selected from a group consisting of Polyimide, Polyetherimide, Polyether sulfone, Polyamide, Polyamide-imide, Polysulfone, Polyphenylsulfone, Polyetherketone, Polyethylene terephthalate, Polyethylene, Polyester, Polyetherester, Polyesteramide, Polymethylmethacrylate, Polypropylene, Polystyrene, Polyvinylchloride or mixtures thereof.

US Pat. No. 10,131,449

ACTUATOR MOUNTING METHOD AND METHOD FOR PRODUCING AN ICE PROTECTION DEVICE AS WELL AS MOUNTING DEVICE

Airbus Defence and Space ...

10. A mounting device comprising:a punch configure to press, in a planar manner, at least one actuator against an inner face of a skin structure for an aircraft to which the at least one actuator is to be fixedly mounted;
a releasable holder configure to hold the at least one actuator on the punch; and
a press-on unit configured to press the punch with the at least one actuator against the inner face of the skin structure.

US Pat. No. 10,540,218

PROCESSOR SYSTEM AND METHOD FOR MONITORING PROCESSORS

Airbus Defence and Space ...

1. A processor system, comprising:at least one application processor, which comprises at least one processor core and a plurality of hardware performance counters; and
a monitoring processor, which is coupled to the at least one application processor by a data-transmission interface, and which comprises:
a look-up table, in which target performance profiles of progression over time of performance events of at least one of the plurality of hardware performance counters are stored for an application which is to be executed on the at least one application processor and monitored, and
an evaluating logic which is linked to the look-up table and is configured to record the progression over time of performance events of the at least one of the plurality of hardware performance counters during execution of the application to be monitored on the at least one application processor and to compare the progression with the target performance profiles stored in the look-up table;
wherein the data-transmission interface is a debug interface of the application processor.

US Pat. No. 10,439,841

NETWORK INTERFACE, NETWORK AND METHOD FOR DATA TRANSMISSION WITHIN THE NETWORK

Airbus Defence and Space ...

1. A network having a multiplicity of network users connected to one another in a ring arrangement, each of the network users comprising:a first physical interface for connecting a network interface of a corresponding network user to a network interface of a second network user;
a second physical interface for connecting the network interface of the corresponding network user to a network interface of a third network user;
at least one data selector connected to the first physical interface via a first data connection line and to the second physical interface via a second data connection line, the at least one data selector comprising a data receiver configured for providing a data receiving connection to at least one of the first and second physical interfaces, and a data transmitter configured for providing a data transmitting connection to at least one of the first and second physical interfaces; and
at least one data switch connected to the at least one data selector via at least a third data connection line and configured for receiving incoming data from the at least one data selector or transmitting outgoing data to the at least one data selector,
wherein the at least one data selector is configured for forwarding data received from one of the first or second physical interfaces to one of the second or third network users and to the at least one data switch,
wherein the at least one data selector is further adapted to duplicate the data received from one of the first or second physical interfaces in a downlink and to forward the received data to one of the second or third network users and the at least one data switch, without an intermediate storage,
wherein at least one of the network users is a server network user and other network users are client network users, and
wherein after an occurrence of a defect, the client network users, which are arranged in the network in a data flow direction downstream of a position of the defect, are configured to reverse the data flow direction, so that one of the first and second physical interfaces, which was adapted before the reversal, to provide a data receiving connection in the downlink, is adapted to provide a data transmitting connection, and the other of the first and second physical interfaces, which was adapted before the reversal, to provide a data transmitting connection in the downlink, is adapted to provide a data receiving connection, and
the server network user in the downlink is configured to send data to the client network users in both a downstream direction of the position of the defect and an upstream direction of the position of the defect.

US Pat. No. 10,432,253

NOISE DISTRIBUTION SHAPING FOR SIGNALS, PARTICULARLY SPREAD SPECTRUM SIGNALS LIKE CDMA SIGNALS, WITH IMPROVED ROBUSTNESS

AIRBUS DEFENCE AND SPACE ...

1. A method for noise distribution shaping for signals comprising the acts ofgenerating a blanking control signal by comparing a received signal comprising transitions with at least one blanking threshold,
determining transitions of the received signal and zones around the determined transitions, and generating a transitions control signal comprising the determined transitions and zones,
adapting the at least one blanking threshold or the received signal according to an offset value depending on the amplitude of the received signal and on the transitions control signal, and
modifying the noise distribution of the received signal by applying blanking of the received signal under control of the blanking control signal.

US Pat. No. 10,213,972

FIBER COMPOSITE LAMINATE AND METHOD FOR PRODUCING A FIBER COMPOSITE LAMINATE

AIRBUS DEFENCE AND SPACE ...

1. A method for producing a fiber composite laminate, comprising:applying at least one of pressure or heat to a first preform, which has one or more dry fiber layers and a thermoplastic elastomer, such that the thermoplastic portion of the thermoplastic elastomer completely impregnates the dry fiber layers of the first preform in at least one first region and only partially impregnates said dry fiber layers in at least one second region; and, in a thermosetting polymer matrix, and
impregnating and curing the fiber layers of the second region of the first preform that are still dry and have not been impregnated with the thermoplastic portion of the thermoplastic elastomer.

US Pat. No. 10,166,724

METHOD FOR PROVIDING SPACERS

Airbus Defence and Space ...

1. A method for providing spacers on a construction component to be adhered, the method comprising:placing a planar formation on the construction component to be adhered, wherein the planar formation comprises passages, wherein the planar formation comprises fibers, wherein the fibers are fluoropolymer fibers; and
introducing a curable liquid into the passages of the planar formation so that the liquid forms spacers on the construction component to be adhered after curing and peeling off of the planar formation, the spacers ensuring a predetermined bond gap thickness.

US Pat. No. 10,109,207

METHOD AND DEVICE FOR AN AIRCRAFT FOR HANDLING POTENTIAL COLLISIONS IN AIR TRAFFIC

Airbus Defence and Space ...

14. An aircraft comprising at least two redundant devices for an aircraft for handling potential collisions in air traffic, the at least two redundant devices each comprising:a collision avoidance system comprising at least one sensor to detect a position of one or more intruders, the collision avoidance system being configured to provide a collision avoidance maneuver to avoid a collision with the one or more intruders;
an onboard flight system configured to provide flight management constraints;
a navigation system configured to provide flight situation data;
an avoid modification processing unit comprising at least one receiver configured to receive at least one of the collision avoidance maneuver, the flight situation data, and the flight management constraints,
wherein the avoid modification processing unit is configured to generate a modified collision avoidance maneuver based on at least one of the collision avoidance maneuver, the flight situation data, and the flight management constraints;
an auto pilot or flight control computer for executing the modified collision avoidance maneuver provided by the avoid processing unit; and
a warning function configured to bring the collision avoidance maneuver from the collision avoidance system and the modified collision avoidance maneuver to attention of a human controller, who can manually override execution of the modified collision avoidance maneuver to follow the collision avoidance maneuver,
wherein the flight management constraints comprise a constraint of the collision avoidance maneuver in a vertical dimension and/or a constraint of the collision avoidance maneuver in a horizontal dimension, based on which the aircraft does not leave vertical and/or horizontal corridors.

US Pat. No. 10,551,369

PROBABILISTIC DEFECT DETECTION IN LAID FIBER RIBBONS

Airbus Defence and Space ...

11. An inspection device for checking fiber composite workpieces, the inspection device comprising:at least one sensor device configured for scanning at least one surface profile of a workpiece; and
at least one computer unit which is in electronic communication with a database and configured to implement a method for probabilistic detection of defects in ribbons of material which have been laid on a fiber composite workpiece, the method comprising:
detecting at least one surface profile of a workpiece having laid material ribbons;
locating a surface profile entry in the database, wherein the surface profile entry provides an assignment of the at least one surface profile that was detected to a defect type and to a hit probability that the at least one surface profile that was detected is based on a defect of the defect type;
the method being performed for examining the fiber composite workpiece; and
displaying an output comprising at least one defect type being assigned to the surface profile entry and the hit probability on an output device;
wherein the surface profile entry is a first surface profile entry, the defect type is a first defect type and the hit probability is a first hit probability, and wherein the method comprises locating at least one further surface profile entry in the database, the at least one further surface profile entry providing an assignment of the surface profile entry to at least one further defect type which is different from the first and provides at least one further hit probability that the at least one surface profile that was detected is based on a defect of the at least one further defect type;
totaling the first hit probability and the at least one further hit probability to create a totaled hit probability;
establishing that the totaled hit probability reaches or exceeds a predetermined limit; and
outputting the totaled hit probability and associated defect types.

US Pat. No. 10,434,729

DEVICES AND METHODS FOR DEPOSITING REINFORCING FIBER TAPES AND DETECTING LAYING ERRORS

Airbus Defence and Space ...

1. A device for automatically depositing of reinforcing fiber tapes on a support by a laying head, the device comprising:at least one roller assigned to the laying head;
at least one radiation source; and
at least one sensor,
wherein, for detection of laying errors, the at least one radiation source and the at least one sensor are integrated into the at least one roller,
wherein the at least one roller is transmissive for radiation emitted by the radiation source, at least in regions thereof, and
wherein radiation emitted from the at least one radiation source and reflected from at least one deposited reinforcing fiber tape as diffuse and/or direct reflection radiation is detectable by the at least one sensor for the detection of laying errors.

US Pat. No. 10,411,791

DUAL-FREQUENCY DOWNLINK TRANSMITTER

AIRBUS DEFENCE AND SPACE ...

1. A transmitter for a dual-frequency satellite-to-earth downlink, the transmitter comprising:a plurality of modulators, wherein each of the plurality of modulators is configured
to modulate respective input data onto a respective one of a first plurality of signals in a first frequency band and to modulate the respective one of the first plurality of signals onto a respective one of a second plurality of signals in a second frequency band, or
to modulate respective input data onto a respective one of a first plurality of signals in a first frequency band and to modulate the respective input data onto a respective one of a second plurality of signals in a second frequency band;
a first plurality of amplifiers, wherein each of the first plurality of amplifiers is configured to amplify a respective one of the first plurality of signals to at least a first predetermined signal strength;
a second plurality of amplifiers, wherein each of the second plurality of amplifiers is configured to amplify a respective one of the second plurality of signals to at least a second predetermined signal strength; and
wherein a number of the plurality of modulators is smaller than a sum of a number of the first plurality of amplifiers and the second plurality of amplifiers.

US Pat. No. 10,399,692

AIRCRAFT FUEL SYSTEM WITH HEATING OF STORED FUEL

AIRBUS DEFENCE AND SPACE ...

1. An aircraft fuel system, comprising:a fuel storage tank arrangement,
a collector fuel tank arrangement,
a first fuel line connecting the fuel storage tank arrangement to the collector fuel tank arrangement, and
a second fuel line connecting the collector fuel tank arrangement to an aircraft engine in use of the aircraft fuel system,
wherein the aircraft fuel system further comprises a first heat-transfer arrangement arranged to transfer heat energy within unspent fuel output from the aircraft engine to fuel within the fuel storage tank arrangement,
wherein a third fuel line is provided that connects the aircraft engine to the collector fuel tank arrangement in use of the system, whereby at least a portion of unspent fuel output by the aircraft engine is returned to the collector fuel tank arrangement, and
wherein the first heat-transfer arrangement comprises:
a fuel line arrangement arranged to draw fuel from, and return that fuel to the fuel storage tank arrangement; and
a heat-exchanger is arranged to thermally couple fuel in the third fuel line to fuel in the fuel line arrangement.

US Pat. No. 10,399,299

SANDWICH COMPONENT AND METHOD FOR PRODUCING A SANDWICH COMPONENT

Airbus Defence and Space ...

1. A sandwich component, comprising:a first cover layer, a second cover layer, and a core disposed therebetween, wherein
the first and second cover layers are each formed from an outer layer made of a fiber-reinforced high-melting-point thermoplast material and, fused therewith, an inner layer made of a low-melting-point thermoplast material,
the core has outer layers each of which is formed from a low-melting-point thermoplast material, and an inner structure, which is formed entirely or partially from a high-melting-point thermoplast material,
the inner layers of the cover layers are each fused with one of the outer layers of the core, and
the core is a honeycomb core, which is a folded honeycomb structure, which is provided by reshaping a film of high-melting-point thermoplast material coated with a low-melting-point thermoplast material, this coating being carried out only in regions, according to the specific shaping process, such that the low-melting-point thermoplast material is present on the finished folded honeycomb structure only in the region of the folded honeycomb structure cover layers, but not in the region of the inner structure of the folded honeycomb structure.

US Pat. No. 10,364,018

COUPLING DEVICE, WING ASSEMBLY FOR AN AIRCRAFT COMPRISING SUCH COUPLING DEVICE AND AIRCRAFT COMPRISING SUCH WING ASSEMBLY

Airbus Defence and Space ...

1. A coupling device for supporting a first component against a second component of an aircraft wherein the first component and the second component are movable relative to each other and exposed to aerodynamic loads, the coupling device being configured for passive flight load alleviation and comprising:a housing comprising a chamber, wherein the chamber comprises a first portion and a second portion and is filled with a fluid;
a piston device movably arranged in the chamber, wherein the piston device separates the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion and defined by at least one wall of the housing;
a first pressure relief valve arranged in the first fluid pathway, wherein the first pressure relief valve is configured to block the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure, and to open the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure.

US Pat. No. 10,344,369

STRUCTURE OR COMPONENT FOR HIGH TEMPERATURE APPLICATIONS, AS WELL AS METHODS AND APPARATUS FOR PRODUCING SAME

Airbus Defence and Space ...

1. A method for producing a structure for high temperature applications comprising a base structure which includes a ceramic composite material and a coating, the method comprising:providing the base structure of the ceramic composite material including a ceramic fiber composite material;
coating the base structure with an ultra high temperature ceramic coating of a coating material which contains at least a metal-semimetal compound, at least a metal boride, at least a metal carbide or at least a metal nitride, by
installing the base structure in a vacuum process chamber for plasma beam techniques,
providing a plasma torch with a cathode, an elongated plasma channel downstream of the cathode to guide the plasma beam, and an ultrasonic nozzle downstream of the elongated plasma channel,
introducing the coating material into the elongated plasma channel and forming a gas mixture in the elongated plasma channel,
expanding the gas with coating material via the ultrasonic nozzle, and
plasma coating the base structure with the coating material.

US Pat. No. 10,328,682

SENSOR INTEGRATION IN THE JOINING OF STRUCTURAL ELEMENTS

Airbus Defence and Space ...

1. A method for joining structural elements into a component made of at least one fiber-reinforced plastics material, the method comprising:providing at least two structural elements made of at least one fiber-reinforced plastics material having a particular matrix;
providing at least one sensor film element made of a thermoplastic material;
arranging the at least one sensor film element on a surface of one of the structural elements or between surfaces to be joined of the at least two structural elements to be joined; and
producing the component in a curing process, wherein the at least one sensor film element is fused with the structural elements arranged on each side thereof such that the at least one sensor film element is integral to the component produced.

US Pat. No. 10,322,550

APPARATUS AND METHOD FOR INFILTRATION OF FIBER MATERIAL WITH RESIN FOR THE PRODUCTION OF A FIBER COMPOSITE COMPONENT

Airbus Defence and Space ...

1. A device configured to infiltrate a fibrous material with resin for the production of a fiber composite component, wherein the device comprises a mold tool with a cavity which is enclosed by at least two tool parts,wherein the mold tool is configured for a relative movement of the at least two tool parts such, in a first tool position, a space is provided inside the cavity to hold the fibrous material, and an additional space is provided to accommodate resin, and wherein a size of the cavity can be reduced by a movement of the mold tool from the first tool position into a second tool position,
wherein a self-contained flow promoter is inserted into the cavity,
said flow promoter comprising at least one first layer and one second layer, connected to each other in an edge region of the flow promoter to enclose a flow space,
wherein the first layer is impermeable to resin and is formed by a plastic film while the second layer is also formed by a plastic film and provides an outlet for guiding resin out of the flow space and into the fibrous material, and
wherein the flow space of the flow promoter is filled with resin and/or the flow promoter has an inlet for conveying resin into the flow space.

US Pat. No. 10,319,246

UNMANNED AERIAL VEHICLE AND METHOD FOR SAFELY LANDING AN UNMANNED AERIAL VEHICLE

Airbus Defence and Space ...

1. An unmanned aerial vehicle, comprising:a lift and propulsion system; and
a flight control system with:
a flight control unit;
a navigation system;
a communication system; and
an actuator system;
wherein the flight control unit is configured for calculating, based on data from the navigation system and/or data of a ground control station configured to control and/or monitor the aerial vehicle, control commands and supplying the control commands to the actuator system for actuating the lift and propulsion system;
further comprising a monitoring unit configured to monitor the communication system to determine whether all communication links of a multiplicity of communication links between the aerial vehicle and the ground control station are interrupted; and
wherein the monitoring unit is configured to select, in response to determining an interruption on all communication links of the multiplicity of communication links, a suitable landing site based on stored data and in accordance with defined rules for landing site selection, wherein the stored data includes current flight conditions data and nearby landing sites data, and wherein the stored data and the defined rules for landing site selection are mirrored on the ground control station, and wherein the monitoring unit is configured to cause the flight control unit to land the aerial vehicle safely at the selected landing site, and
wherein the flight control unit is configured for determining a flight route to the selected landing site, wherein determination of the flight route is carried out according to defined rules for flight route determination, and wherein the defined rules for flight route determination are mirrored on the ground control station with the stored data and the defined rules for landing site selection and the ground control station is configured determine the same flight route and the same selected landing site as determined by the unmanned aerial vehicle in response to determining an interruption on all communication links of the multiplicity of communication links.

US Pat. No. 10,694,615

ELECTRICALLY CONNECTING MULTI-LAYER INSULATION BLANKETS

Airbus Defence and Space ...

1. An apparatus comprising:at least two multi-layer insulation (MLI) blankets, including a first MLI blanket and a second MLI blanket, each MLI blanket having at least two bonding points, including a first bonding point and a second bonding point of the first MLI blanket, and a first bonding point and a second bonding point of the second MLI blanket;
wherein the second MLI blanket further has a grounding point configured to be grounded;
wherein the first bonding point and the second bonding point of the first MLI blanket are each electrically connected to either or both of the first bonding point and the second bonding point of the second MLI blanket; and
wherein the first bonding point and the second bonding point of the second MLI blanket are each electrically connected to either or both of the first bonding point and the second bonding point of the first MLI blanket.

US Pat. No. 10,556,669

ACTUATOR ASSEMBLY

Airbus Defence and Space ...

1. An actuator assembly for manipulating a fluid flowing around a flow body, part of the fluid being receivable in a volume of at least one cavity arranged in the flow body, andthe fluid passing through at least one opening in the cavity during manipulation of the fluid,
the volume of the cavity being changeable by moving a wall portion defining the cavity at least in part, comprising:
a drive unit with at least one actuator; and
a coupling element connecting the at least one actuator to the wall portion,
the at least one actuator executing a periodic movement over time when actuated, and
the periodic movement causing a translational movement of the wall portion defining the cavity,
wherein the wall portion is topologically shaped to correspond to a shape of the cavity, such that a distance between the wall portion and an edge region of the cavity is always less than a distance between the wall portion and a region of the opening.

US Pat. No. 10,442,540

DEVICE AND METHOD FOR DEICING AND/OR PREVENTING ICE FORMATION AND PROFILE ELEMENT AND AIRCRAFT HAVING SUCH A DEVICE

Airbus Defence and Space ...

1. A device for de-icing or for preventing ice formation for an aircraft, comprising:a heat emitting device configured to emit heat at a surface region of the aircraft,
wherein the heat emitting device comprises at least one elongated heat source and a heat insulating jacket covering the heat source except at a linear opening that is substantially narrower than the width of the heat source, the heat insulating jacket directing the emitted heat through the linear opening only, thereby defining a line-shaped heat emission region corresponding to the linear opening, the line shaped heat emission region delineating a predetermined breaking point or a predetermined breaking line in ice accumulating along the line-shaped heat emission region on the surface region,
wherein the line-shaped heat emission region is a heat emission line having a width of no more than 5 mm; and
a deformation device, comprising a first deformation unit on a first adjacent unheated side of the heat emission line, that deforms a first section of the surface region located on the first adjacent unheated side, and a second deformation unit, on a second adjacent unheated side of the heat emission line, that deforms a second section of the surface region located on the second adjacent unheated side.

US Pat. No. 10,427,332

FIBER PLACEMENT AND PRODUCTION METHOD

Airbus Defence and Space ...

1. A fiber placement method for automatic placement of fibers onto a work surface by a fiber application and/or compaction roller having a fiber contact surface formed at a circumference of the fiber application and/or compaction roller, the method comprising:a) applying and pressing fibers provided with adhesive, binder, matrix, or resin material by the transparent circumferential fiber contact surface; and
b) guiding activation radiation starting from an interior of the fiber application and/or compaction roller through the transparent circumferential fiber contact surface for activating the adhesive, binder, matrix, or resin material.

US Pat. No. 10,280,969

HYBRID METAL-COMPOSITE DRIVE SHAFT UNIT AND METHOD OF MANUFACTURING SAME

Airbus Helicopters Deutch...

1. A hybrid metal-composite drive shaft unit for power transmission in a rotary-wing aircraft, the hybrid metal-composite drive shaft unit comprising:at least one metal drive shaft connector that is at least partly embedded into a composite drive shaft,
wherein the composite drive shaft comprises a thermoplastic polymer being welded to the at least one metal drive shaft connector, wherein a welded connection is provided that defines a first load path for transmission of loads between the at least one metal drive shaft connector and the composite drive shaft,
wherein the at least one metal drive shaft connector and the composite drive shaft comprise, in the region of the welded connection, at least partly a polygonal cross-sectional shape for forming a form-fit connection that defines a second load path for transmission of loads between the composite drive shaft and the at least one metal drive shaft connector.

US Pat. No. 10,217,442

METHOD FOR THE COMMON REPRESENTATION OF SAFETY-CRITICAL AND NON-SAFETY-CRITICAL INFORMATION, AND DISPLAY DEVICE

Airbus Defence and Space ...

1. A method for the common representation of safety-critical and non-safety-critical information on a display unit of a vehicle, comprising:receiving non-safety-critical information by a first processor and producing at least one graphic presentation of the non-safety-critical information;
receiving safety-critical information by a second processor, wherein the second processor also receives the at least one graphic presentation of the non-safety-critical information;
producing at least one graphic presentation of the safety-critical information;
representing the presentations of safety-critical and non-safety-critical information on the display unit, the representation having at least two representation planes;
presenting the non-safety-critical information on a rear, in a direction of view of the observer, plane of the at least two representation planes, and presenting the safety-critical information on a front representation plane; and
checking whether the safety-critical information is recognizable, in a case of an at least partial overlap of the presentation of the non-safety-critical information by the presentation of the safety-critical information;
wherein if during the checking step a determination is made that the presentation of the non-safety-critical information is overlapped by the presentation of the safety-critical information, adapting at least the overlapping parts of the presentation of the safety-critical information in such a way that the safety-critical information is recognizable;
adapting parts of the presentation of the safety-critical information by modifying the graphic presentation of the safety-critical information in the overlapping region such that the graphic presentation of the overlapping parts, as such, is modified;
wherein the modification of the graphic presentation of the safety-critical information in the overlapping region takes place through at least one of a color modification, a line modification, a size modification, a contrast modification, or a modification of the representation frequency.

US Pat. No. 10,464,269

LAYING DIE, LAYING DEVICE AND METHOD FOR MANUFACTURING A LAYING DIE

AIRBUS DEFENCE AND SPACE ...

1. A laying die for picking up and laying of substrates, the laying die comprising:an elastically deformable substrate receiving structure configured to provide an engagement surface to releasably receive substrates;
an attaching element comprising a gas channel configured to provide positively or negatively pressurized gas to pick up and blow off the substrates;
a carrier body made from an elastically deformable material, the carrier body being sandwiched between the substrate receiving structure and the attaching element, the attaching element being arranged to distribute the positively or negatively pressurized gas over the carrier body, and the carrier body comprising a plurality of breakthroughs to transfer the positively or negatively pressurized gas from the attaching element to the substrate receiving structure, and the substrate receiving structure comprising an elastically deformable distribution plate to distribute the positively or negatively pressurized gas over the engagement surface of the substrate receiving structure; and
a cambering device configured to deform at least one of the carrier body and the substrate receiving structure according to a predetermined deformation after the substrates are picked up by the laying die, the cambering device comprising a rope attached to the substrate receiving structure, and configured to pull the at least one of the carrier body and the substrate receiving structure into the predetermined deformation.

US Pat. No. 10,435,169

HYBRID ELECTRIC DRIVE TRAIN FOR VTOL DRONES

Airbus Defence and Space ...

1. A vertical take-off aircraft, comprising:a propulsion drive for generating a driving force effective in a horizontal direction;
a lift drive for generating a lifting force effective in a vertical direction;
a motor for providing mechanical energy for the propulsion drive;
a first shaft mechanically coupled to the motor and to the propulsion drive;
a first generator for providing electrical energy for the lift drive;
an exhaust gas turbocharger for the motor, the exhaust gas turbocharger comprising a first turbine driven by an exhaust gas flow of the motor and a compressor driven by the first turbine, the compressor configured to increase the working pressure in the motor;
a second shaft, wherein the compressor is directly driven by the first turbine via the second shaft; and
a gearing mechanism mechanically coupled directly to the first shaft and the second shaft,
wherein the first turbine is mechanically coupled to a second shaft for transmitting mechanical energy via the first shaft and the gearing mechanism to the propulsion drive.

US Pat. No. 10,429,265

COMPONENT DEVICE AND METHOD FOR DETECTING A DAMAGE IN A BONDING OF A COMPONENT DEVICE

AIRBUS DEFENCE AND SPACE ...

1. A component device for a primary supporting component of an aircraft, comprising:a first component element;
a second component element;
a bonding which provides a connection between the first component element and the second component element; and
a detector device with at least one interior space sensor device that measures a change of the pressure and/or of a concentration of a gas surrounding the interior space sensor device;
wherein the first component element, the second component element, and the bonding confine an interior space;
wherein the interior space sensor device is arranged in the interior space;
wherein the interior space sensor device comprises a first interior space sensor that measures the absolute pressure of the gases surrounding the first interior space sensor, a second interior space sensor that measures the partial pressure of a gas surrounding the second interior space sensor, and a third interior space sensor that measures the concentration of a gas surrounding the third interior space sensor; and
wherein the interior space sensor device comprises a plurality of different second interior space sensors, each of which is configured to measure the partial pressure of a different gas, and/or a plurality of different third interior space sensors, each of which is configured to measure the concentration of a different gas.

US Pat. No. 10,427,779

AIRCRAFT WING WITH AN ADAPTIVE SHOCK CONTROL BUMP

Airbus Defence and Space ...

1. An aircraft wing with an upper surface element and a first actuator powered mechanism for varying the shape of the upper surface element, wherein the surface element comprises:an upstream segment SEG1 with a stiffness S1;
a downstream segment SEG2 with a stiffness S2;
an interconnecting segment SEG3 with a stiffness S3, the interconnecting segment SEG3 interconnecting a downstream edge of SEG1 with an upstream edge of SEG2, wherein the interconnecting segment SEG3 extends along the whole downstream edge of SEG1 and the whole upstream edge of SEG2, or at least along a major part of the downstream edge of SEG1 and a major part of the upstream edge of SEG2, and the interconnecting segment SEG3 exhibits a mechanical pretension causing a convex shape of the upper surface element, with: S3 a link element LNK, the link element LNK interconnecting an upstream edge of SEG1 with an upper surface of the aircraft wing;
wherein the first actuator powered mechanism interconnects a contact C1 on a lower side of the upper surface element with a contact C2 on an inner structure of the aircraft wing,
wherein the first actuator powered mechanism controls the shape of the upper surface element by controlling the distance between C1 and C2, and
wherein the downstream segment SEG2 comprises:
an upstream segment SEG1* with a stiffness S1;
a downstream segment SEG2* with a stiffness S2; and
an interconnecting segment SEG3* with a stiffness S3, the interconnecting segment SEG3* interconnecting a downstream edge of SEG1* with an upstream edge of SEG2*, wherein the interconnecting segment SEG3* extends along the whole downstream edge of SEG1* and the whole upstream edge of SEG2*, or at least along a major part of the downstream edge of SEG1* and a major part of the upstream edge of SEG2*, and the interconnecting segment SEG3* exhibits a mechanical pretension causing a convex shape of the upper surface element, with: S3

US Pat. No. 10,416,793

SELECTION UNIT TO SELECT OR CONTROL DIFFERENT STATES OR FUNCTIONS OF AN AIRCRAFT SYSTEM

Airbus Defence and Space ...

1. A selection unit to select a state from a plurality of different states of an aircraft system, the selection unit comprising:a manually operable selection element, the selection element comprising a first display unit configured to present a selection indication of a selected state from a plurality of different states associated with the aircraft system based on a physical actuation of the selection element, wherein an actual state of the aircraft system depends on the selected state of the selection element, wherein the selection element is further configured for dynamic electronic selection of the selected state based on an external signal input; and
a second display unit co-located with the selection element so that the selection element is disposed within and surrounded by the second display unit, the second display unit configured to visualize subsystems of the aircraft system in the actual state of the aircraft system selected depending on the selected state of the selection element.

US Pat. No. 10,414,516

LANDING DEVICE FOR LANDING A SPAN-WISE LOADED AIRCRAFT

AIRBUS DEFENCE AND SPACE ...

1. A landing device for landing an aircraft thereon, the landing device comprising:a first group of three or more supporting elements comprising elongated generally vertically arranged solid members having an axial length arranged next to each other in a first direction, each supporting element configured to directly engage and support a portion of a body or a portion of a wing of the aircraft,
wherein each supporting element is further configured to bow along the axial length when loaded by the mass of the body portion or the wing portion supported by the respective supporting element.

US Pat. No. 10,416,310

INTEGRATED POSITIONING SOLUTION FOR GLOBAL NAVIGATION SATELLITE SYSTEMS

AIRBUS DEFENCE AND SPACE ...

1. A process for an own global navigation satellite system and at least one other global navigation satellite system, said process comprising:receiving ranging signals including only encrypted navigation data or no navigation data from the at least one other global navigation satellite system;
processing the received ranging signals from the at least one other global navigation satellite system in a manner similar to the processing of navigation messages from ranging signals of the own global navigation satellite system to compute navigation messages for the at least one other global navigation satellite system for users of the own global navigation satellite system; and
transmitting the computed navigation messages of the at least one other global navigation satellite system from satellites of the own global navigation satellite system.

US Pat. No. 10,399,288

LAYING UNIT AND METHOD FOR PRODUCING A FIBRE COMPOSITE COMPONENT

Airbus Defence and Space ...

1. A laying unit for producing a fibre composite component, comprising:a cylindrical housing configured to unroll on a surface; and
a plurality of fibre coils configured so as to be able to be unwound during a movement of the laying unit, wherein the fibre coils are provided in a movably mounted manner inside the housing.

US Pat. No. 10,393,541

AIRCRAFT NAVIGATION SYSTEM AND METHOD FOR AIRCRAFT NAVIGATION

Airbus Defence and Space ...

1. An aircraft navigation system comprising:a navigation-map data source, navigation-map data provided by the navigation-map data source including information about a multitude of objects O on earth surface which are of high potential visibility and high potential identifiability from positions elevated relative to the earth surface, each information for an object O?O including a position and a type of the respective object O;
a first system for measuring an actual aircraft position P(t) at time t;
a waypoint data source providing a plurality of waypoints WPi defining an aircraft intended flight track, wherein i is an integer and WPi represents one of the plurality of waypoints;
a second system for selecting per waypoint WPi one object Oi(WPi) with Oi(WPi)?O depending on given selection criteria, wherein Oi(WPi) represents an object Oi selected for the waypoint WPi and is one of the multitude of objects O; and
a display for displaying an information I(Oi(WPi) referring the selected object Oi(WPi), wherein I(Oi(WPi) represents information I referring to the object Oi selected for the waypoint WPi,
wherein a ranking index of each object O?O concerning its potential visibility and potential identifiability is based on at least one of the following:
a relative size of the object O compared to an environment E(O) of the object O;
a visible brightness contrast;
a visible colour contrast between the object O and the environment E(O) of the object O; or
a geometric shape of the object O, and
wherein the selection criteria consider
a distance di,n between a waypoint WPi and positions of neighbouring objects On(WPi) being positioned within a given maximum distance from the respective waypoint WPi, with On?O, wherein n is an integer, On(WPi) is one of objects from the plurality of object O within the given maximum distance from the waypoint WPi, di,n is a distance a given object On and the waypoint WPi, and wherein On is a sub-set of the set O, and/or
the ranking index of the neighbouring objects On(WPi) concerning their potential visibility and potential identifiability.

US Pat. No. 10,371,066

UNMANNED AIRCRAFT AND OPERATION METHOD FOR THE SAME

Airbus Defence and Space ...

1. An unmanned aircraft, comprising:a propulsion system that comprises a diesel or kerosene internal combustion engine, wherein the propulsion system is a hybrid propulsion system which, in addition to the internal combustion engine, comprises an electric motor and an energy storage device configured to store electric energy for driving the electric motor;
a charging device configured to charge the internal combustion engine of the unmanned aircraft; and
a controller configured to control the charging device or the hybrid propulsion in accordance with flight operation parameters,
wherein the charging device is designed for multi-stage charging,
wherein the charging device comprises multiple exhaust gas turbines that are connected in series,
wherein the charging device additionally comprises at least one mechanical charger configured to be driveable by the electric motor of the hybrid propulsion, and
wherein the controller is configured to control charging of the charging device with or without the use of exhaust gas energy and by the use of mechanical energy from the internal combustion engine or from the electric motor.

US Pat. No. 10,330,909

DEVICE FOR MICROSCOPIC EXAMINATION

AIRBUS DEFENCE AND SPACE ...

1. A device for microscopic examination, comprising: an image output unit having a camera; a multiple carrier structure; a first object carrier unit, mounted to the multiple carrier structure, including a primary first sample container attached to the first object carrier unit, configured to support a primary first sample in a stationary manner in the first sample container, and a second object carrier unit, mounted to the multiple carrier structure, including a secondary first sample container attached to the second object carrier unit, configured to support a secondary first sample in a stationary manner in the secondary first sample container; a first image input unit, which is mounted at least substantially rotationally to the first allocated object carrier unit; a second image input unit, which is mounted at least substantially rotationally to the second allocated object carrier unit; a coupling unit coupler configured to selectively optically couple the image output unit and one of the first and second image input units to form a microscope unit; at least one deflection element deflector configured to deflect a beam path of an image, whereby the deflection element deflector sets an image transmission path that contains a change of direction, which enables the optical coupling; and at least one derotator unit arranged in a beam path between at least one of the first and second image input units and the image output unit, wherein the first and second object carrier units are embodied as centrifuges, the image output unit is static, while the image input unit is rotationally coupled to an allocated object carrier unit, and has an ocular lens configured to magnify an image of one of the samples picked up by one of the first and second image input units, and the first and second image input units are configured to rotate relative to the whole image output unit at the same rotational speed as the respective first and second object carrier units.