US Pat. No. 9,227,740

DEVICE FOR MONITORING THE ATTITUDE OF A SATELLITE, AND METHOD FOR CONTROLLING A SATELLITE PROVIDED WITH SAID DEVICE

AIRBUS DEFENCE AND SPACE ...

1. Device for controlling the attitude of a satellite exploiting solar pressure, comprising at least two solar generators
arranged on either side of a central body of the satellite, extending along a rotation axis of said solar generators, each
solar generator having one face to be exposed to the Sun, referred to as “front face”, said device further comprising at least
three surfaces whose optical properties can be commanded, wherein said surfaces whose optical properties can be commanded
are arranged:
on flaps connected to solar generators, each flap being fixed with respect to the solar generator to which said flap is connected,
and

such that at least two of said surfaces whose optical properties can be commanded are not parallel when the front faces of
the solar generators are parallel,

wherein said device comprises a command module adapted to command separately the optical properties of each surface whose
optical properties can be commanded, said command module being configured to command said surfaces whose optical properties
can be commanded so as to create torques around three independent axes without de-pointing the solar generators with respect
to the Sun.

US Pat. No. 9,365,301

METHOD OF COMMAND OF MAGNETO-TORQUERS OF AN ATTITUDE CONTROL SYSTEM OF A SPACE VEHICLE

AIRBUS DEFENCE AND SPACE ...

1. A method of commanding magneto-torquers of an attitude control system of a space vehicle subjected to an external magnetic
field of variable direction, comprising the steps of:
controlling an attitude of the space vehicle by said magneto-torquers;
forming, in cooperation with a local external magnetic field, magnetic torques in a local control plane orthogonal to a direction
of the local external magnetic field;

measuring the local external magnetic field;
determining a magnetic torque to be formed in the local control plane as a function of a desired three-axes attitude control
torque;

commanding the magneto-torquers to form, in cooperation with the local external magnetic field, the determined magnetic torque;
and

wherein the magnetic torque to be formed in the local control plane is determined as a function of a locally uncontrollable
component of the desired attitude control torque which is orthogonal to the local control plane, the contribution of the locally
uncontrollable component to the magnetic torque to be formed being non-zero when the locally uncontrollable component is non-zero.

US Pat. No. 9,281,721

PERMANENT-MAGNET ELECTRIC MOTOR COMPRISING A SEGMENTED STATOR

AIRBUS DEFENCE AND SPACE ...

1. An electric motor (1) with permanent magnets comprising: a rotor (4), on which permanent magnets (6) are fastened; and
a stator (2), said stator comprising a stator structure and coils (5) arranged onto said stator structure, wherein the stator structure is resulted in an assembly of at least three juxtaposed
stator elements (21) fastened only to a baseplate (3), and wherein each stator element (21):

comprises at least one winding area (211) on a side of a first end of said stator element and a fastening foot (212) on a side of a second end of the stator element, opposite to the first end, the stator element being fastened only to the
baseplate (3) at the second end;

is fastened only to the baseplate (3) with a bearing surface (216) of the fastening foot (212) tight on said baseplate by means of a single fastening element (31) adjusted to a bore (213) crossing said fastening foot; and

wherein the bearing surface (216) enlarged in relation to a cross-section of the stator element in the winding area (211).

US Pat. No. 9,618,601

METHOD AND SYSTEM FOR ESTIMATING THE DIRECTION OF ARRIVAL OF A TARGET SIGNAL RELATIVE TO A SATELLITE

AIRBUS DEFENCE AND SPACE ...

1. A method for estimating a direction of arrival of a target signal with respect to an array of measurement antennas of a
satellite in terrestrial orbit, comprising the steps of:
estimating the direction of arrival of the target signal as a function of measurement signals, corresponding to the target
signal received by respectively at least a first measurement antenna and a second measurement antenna of the array of measurement
antennas;

combining each of the measurement signals with a reference signal corresponding to the target signal received by a reception
antenna of the satellite having a maximum gain greater than respective maximum gains of the first measurement antenna and
of the second measurement antenna; and

estimating the direction of arrival of the target signal on the basis of the signals obtained by combining each of the measurement
signals with the reference signal.

US Pat. No. 9,446,863

SATELLITE HAVING A SIMPLIFIED, STREAMLINED, AND ECONOMICAL STRUCTURE, AND METHOD FOR IMPLEMENTING SAME

Airbus Defence and Space ...

1. A satellite having a structure comprising:
a circular launcher interface ring intended to be removably secured to an analogous ring secured to a satellite launcher,
and

at least two planar equipment-holding primary walls extending substantially parallel to a longitudinal satellite axis of said
circular launcher interface ring and rigidly connected to each other and to said circular launcher interface ring,

wherein each primary wall bears directly on an upper face of said circular launcher interface ring by a base of said primary
wall, said base facing said circular launcher interface ring, and each primary wall is rigidly and directly attached to said
circular launcher interface ring by at least one somewhat point-by-point connection to at least one point or area of tangency
or of intersection between said base of said primary wall and said circular launcher interface ring.

US Pat. No. 9,796,484

SATELLITE SYSTEM COMPRISING TWO SATELLITES ATTACHED TO EACH OTHER AND METHOD FOR LAUNCHING THEM INTO ORBIT

AIRBUS DEFENCE AND SPACE ...

1. A satellite system, comprising:
a first satellite, called carrier satellite; and
a second satellite, called piggyback satellite, said piggyback satellite being releasably fixed to said carrier satellite,
said piggyback satellite being releasable, on command, from said carrier satellite to provoke separation of said carrier satellite
and from said piggyback satellite,

each of said carrier and piggyback satellites comprising an Earth face, wherein,
said piggyback satellite comprises:
a first propulsion system with
a first propellant reserve suitable for keeping said piggyback satellite in orbit, and
said carrier satellite comprises:
a second propulsion system with
a second propellant reserve configured to perform a change of orbit of said carrier satellite and of said piggyback satellite
fixed to said carrier satellite, and

said piggyback satellite is fixed onto the Earth face of the carrier satellite, such that the Earth face of said piggyback
satellite is substantially at right angles to the Earth face of said carrier satellite.

US Pat. No. 9,764,861

SPACE CRAFT COMPRISING AT LEAST ONE PAIR OF SUPPORTING ARMS, SAID ARM PAIR BEING EQUIPPED WITH A HOLLOW MOUNTING MODULE, AND METHOD FOR EMPLOYING SUCH A CRAFT

Airbus Defence and Space ...

1. A space craft capable of being put into orbit around a planet, comprising a body, at least one pair of supporting arms,
a first device mounted on a first supporting arm and a second device mounted on a second supporting arm, said first arm being
rotatably mounted on said body about an axis of rotation, said second arm being fixed to said body, and at least one of said
first device and second device is offset with respect to said axis of rotation of said first arm, wherein said pair of supporting
arms comprises a hollow mounting module for rotatably mounting said first arm on said body, said mounting module comprising
an opening through which said axis of rotation and said second supporting arm pass and comprising means for controlling a
sun-synchronous rotation of said first arm about said axis of rotation, said first device being capable of being interposed
between the sun and said second device throughout the orbit of the craft, so that said second device is at least partially
in a shadow of said first device throughout the orbit of the craft.

US Pat. No. 9,859,973

HYBRID SPACE SYSTEM BASED ON A CONSTELLATION OF LOW-ORBIT SATELLITES WORKING AS SPACE REPEATERS FOR IMPROVING THE TRANSMISSION AND RECEPTION OF GEOSTATIONARY SIGNALS

AIRBUS DEFENCE AND SPACE ...

1. Satellite telecommunications system, comprising:
at least one transmitting/receiving surface terminal associated with a user substantially on a surface of the Earth;
at least one geostationary satellite configured to receive signals from and to transmit signals to a predefined coverage area
with a line of sight to said at least geostationary satellite, and

at least one traveling satellite moving above the surface of the Earth and configured to perform at least one of the following
using a same frequency band: repeat signals received from said at least one transmitting/receiving surface terminal towards
said at least one geostationary satellite, or repeat signals received from said at least one geostationary satellite towards
said at least one transmitting/receiving surface terminal, the same frequency band is used to communicate between said at
least one transmitting/receiving surface terminal and said at least one traveling satellite and between said at least one
traveling satellite and said least one geostationary satellite; and

wherein tracking/telemetry and command signals of said at least one traveling satellite are relayed by said at least one geostationary
satellite.

US Pat. No. 9,492,878

TOOLSET AND METHOD FOR PRODUCING A METAL LINER

AIRBUS DEFENCE AND SPACE ...

1. Toolset for manufacturing a metal liner for a composite vessel, comprising:
a mandrel configured in several mandrel elements forming support elements of primary parts constituting the metal liner, wherein,
the metal liner comprises a vessel liner with rounded ends, and the support elements comprise a front body and a rear body
to receive respectively a first rounded metal liner end and a second rounded metal liner end; and

annular sectors designed to be positioned on junction ends of said front body and rear body to support junction ends of said
first rounded metal liner end and said second rounded metal liner end, wherein the mandrel elements are parts made of a soluble
material.

US Pat. No. 9,188,438

METHOD FOR DETECTING SHIFTS IN LINE IMAGES OBTAINED BY A SENSOR THAT IS AIRBORNE OR MOVING IN SPACE

AIRBUS DEFENCE AND SPACE ...

1. An estimation method for estimating shifts of line images of an image, referred to as a “composite image”, made up of the
juxtaposition of J line images, in which:
the line images show portions of a scene on the surface (S) of a celestial body that are different and successively acquired
by a row of sensitive cells of a sensor (10) on board a vehicle flying over said celestial body, each line image being composed of a plurality of pixels, and

a line image Lj, where 1?j?J, presents a lateral and/or longitudinal shift between the position that line image Lj is destined to occupy in the composite image and the position it should occupy, because of a sighting error of the sensor
(10) during the acquisition of line image Lj,

wherein the lateral and/or longitudinal shift of a line image Lj relative to a line image Li, where j is different from i, is estimated according to a local model of lateral and/or longitudinal variation of the similarity
between different line images,

wherein the local model of lateral and/or longitudinal variation of the similarity between different line images is determined
by calculating similarity values between different line images of the composite image,

a step (20) of estimating the relative lateral shift ?j of line image Lj relative to line image Li, during which the local model of lateral variation of the similarity between successive line images is determined by calculating
similarity values of line image Lj to line image Li for a plurality of lateral translation values of one line relative to the other,

the relative lateral shift ?j is estimated as the lateral translation for which the value of the model of lateral variation of the similarity is maximum,
and

a step (21) of integrating relative lateral shifts ?j in successive line images, for determining cumulative lateral shifts ??j with respect to a reference line image of the composite image.

US Pat. No. 9,961,308

MULTISPECTRAL IMAGE CAPTURE DEVICE COMPRISING A FILTER WHEEL

AIRBUS DEFENCE AND SPACE ...

1. Multispectral image capture device (10), comprising:an image-forming optical system (1, 2), suitable for forming an image in a focal plane (FP);
at least one two-dimensional image sensor (3), comprising a photosensitive surface limited by a peripheral contour (C3), and situated in the focal plane (FP);
a wheel (4) that comprises a plurality of spectral filters (41-46), arranged in order to keep said filters parallel and close to the focal plane (FP) or to an intermediate image plane (IP) of the image-forming optical system (1, 2); and
a drive system (5), arranged in order to rotate the wheel (4) about an axis of rotation (A-A) so as to bring each of the filters (41-46) into the light beam (L);in which at least one of the filters (41-46), called filter having a narrow angular sector, has an angular extension that is less than an angular extension of the photosensitive surface of the image sensor (3) when the filters are close to the focal plane (FP), or that is less than an angular extension of a portion (30) of the intermediate image plane (IP) that is optically conjugated with the entire photosensitive surface by a re-imaging part (2) of the image-forming optical system, the angular extensions being measured with respect to the axis of rotation (A-A) of the wheel (4),the drive system (5) being adapted in order to rotate the wheel (4) continuously while several images are captured successively by the image sensor (3);wherein the image sensor (3) comprises a plurality of separate photosensitive pixels (31) adapted in order to operate each according to an acquisition sequence that comprises successively at least one phase of signal accumulation and one phase of reading an accumulated signal; and the angular extension of the filter having a narrow angular sector is greater than an angle of rotation described by the wheel (4) during a sum of a total period of the acquisition sequence and a period of an additional accumulation phase.

US Pat. No. 9,708,081

RADIATOR WITH REDUCED INSOLATION FOR SATELLITE AND SATELLITE PROVIDED WITH SUCH A RADIATOR

AIRBUS DEFENCE AND SPACE ...

1. Radiator (1) for a satellite (2) intended to be stationed in geostationary orbit around the earth (T) in a plane that is tilted relative to the ecliptic
plane, the radiator (1) comprising at least one panel (4) having at least one radiative surface (5, 6), and comprising:
a support member (7) bearing the at least one panel (4),

control and motorization means (10) for pivoting the support member about an axis of rotation (R),

the radiator being characterized in that the axis of rotation (R) is tilted relative to the at least one radiative surface
(5, 6) and in that the at least one radiative surface (5, 6) of the at least one panel (4) is perpendicular to an axis of radiation (S), the axis of radiation (S) and the axis of rotation (R) being tilted relative
to each other by a non-zero operating angle (?), corresponding to the tilt angle of the orbit plane of the satellite (2) relative to the ecliptic plane, the operating angle (?) being fixed, such that for any rotation of the support member (7) about the axis of rotation (R) using the control and motorization means (10), the at least one radiative surface (5, 6) remains parallel to the ecliptic plane.

US Pat. No. 9,237,117

NETWORK OF SWITCHES AND PAYLOAD OF TELECOMMUNICATIONS SATELLITE COMPRISING A NETWORK OF SWITCHES

AIRBUS DEFENCE AND SPACE ...

1. A network, comprising:
connection switches arranged to provide N input accesses and M output accesses to the network, N and M being integers, N being
a number of input accesses and M being a total number of output accesses,

where P output accesses are selected from the M total output accesses, P being an integer, P?N, and P?M,
each connection switch of the network having four ports and at least two different selectable states that correspond to an
establishment of different internal connections between the four ports, and at least one of said four ports connected to provide
one of said N input accesses or one of said M output accesses, said connection switches arranged as one or more stages of
switches, each stage of switches including:

a pair of lines of interconnection switches, each line being a set of said interconnection switches connected to one another,
and each of said interconnection switches having four ports, none of which are connected as input or output accesses to the
network, and

transverse arms linking the interconnection switches of different lines of a same stage, each transverse arm consisting of
elements that are separate from those of the other transverse arms of the same stage, and each transverse arm comprising a
transverse switch that has at least two links and one switch,

wherein at least two of said transverse switches from different ones of said transverse arms of each of said one or more stages
are connection switches of the network, and

wherein at least one interconnection switch of a first line of any stage of said one or more stages is connected by an inter-line
link to an interconnection switch of a second line of the same stage or of a line of another stage of the network, each inter-line
link being a link having no switch.

US Pat. No. 9,160,443

MULTI-BEAM SATELLITE TELECOMMUNICATIONS SYSTEM AND METHOD FOR FORMING BEAMS

AIRBUS DEFENCE AND SPACE ...

1. A device (20) adapted to be placed on board a multi-beam telecommunications satellite (2) and configured to relay data between terrestrial terminals (T) and at least one ground station (3), said data being exchanged on a radiofrequency user link between the satellite (2) and the terrestrial terminals (T) by forming beams in a down-path and/or up-path of said user link, said device comprising:
an on-board beam forming module (200) for forming beams on board in the satellite;

a ground-formed beam processing module (201) for processing ground-formed beams formed in the ground station (3);

a routing module (202) for routing signals received from any of the at least one ground station (3) and first and second terrestrial terminals (T), signals of beams formed on board to be sent/received by the first terrestrial
terminal being routed towards the on-board beam forming module (200), and signals of ground-formed beams to be sent/received by the second terrestrial terminal being routed towards the ground-formed
beam processing module (201) for processing ground-formed beams; and

an array of antennas (An) for exchanging data on the user link, said array of antennas being used both for the on-board-formed
beams and for the ground-formed beams.

US Pat. No. 9,057,402

SPACERS FOR ROLLING BEARINGS WITH ADJUSTED LENGTHS

AIRBUS DEFENCE AND SPACE ...

1. A rolling bearing device of the type having a central shaft and a hub that are mobile in rotation relative to each other,
comprising:
an upper rolling bearing and a lower rolling bearing, arranged between the central shaft and the hub in two positions spaced
in an axial direction (Z), said upper and lower rolling bearings each having inner and outer rings and each having balls,
the inner ring of each rolling bearing being adjusted around the central shaft and the outer ring of each rolling bearing
being inside the hub,

the upper and lower rolling bearings being mounted back-to-back, a rigid preload being applied to said upper and lower rolling
bearings in the axial direction,

spacers being placed between said upper and lower rolling bearings,
whereby an inner spacer resting, by upper and lower ends of said inner spacer, on the inner rings of the upper and lower rolling
bearings, respectively, and a outer spacer resting, by upper and lower ends of the lower spacer, on the outer rings of the
upper and lower rolling bearings, respectively,

wherein lengths of both the inner and outer spacers are adjusted to limit variations in rigid preload caused by temperature
gradients in the radial direction from one point of the bearing to another to less than 30%, whereby for an optimum length
of the spacers, an effect of differential axial expansion of the spacers on the preload, in a direction of an increased preload,
will offset an effect of differential radial expansion of the rings on the same preload along lines of a decreased preload.

US Pat. No. 9,207,446

SCANNING SPACE OBSERVATION OPTICAL SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. Optical system comprising:
a rotary scanning mirror arranged to receive an incident beam of rays and to return an input beam along a first axis, the
rotary scanning mirror has an axis of rotation aligned on the first axis;

an optical instrument arranged to receive the input beam from the scanning mirror and to return an output beam along a second
axis;

an optical image rotation device positioned on the second axis and arranged to receive the output beam, the optical image
rotation device has an axis rotation aligned on the second axis;

a rotational driving device common to the scanning mirror and to the optical image rotation device about their respective
rotation axes; and

wherein the optical instrument returns the output beam parallel to the input beam, in a direction opposite to the input beam,
towards the optical image rotation device.

US Pat. No. 9,602,189

METHOD AND SYSTEM FOR ESTIMATING A PATH-LENGTH DIFFERENCE OF A TARGET SIGNAL TRANSMITTED BY A SPACECRAFT OR AIRCRAFT

AIRBUS DEFENCE AND SPACE ...

1. A method for estimating a path-length difference between two paths followed by a target signal transmitted by a spacecraft
or aircraft respectively to a first receiving antenna and a second receiving antenna of a receiving base, the method comprising
the steps of:
measuring a useful phase difference between signals corresponding to the target signal received respectively on the first
receiving antenna and the second receiving antenna, each of the first receiving antenna and the second receiving antenna of
the receiving base exhibits a main radiation lobe of a width equal to or greater than 20°;

estimating the path-length difference as a function of useful phase difference measurements to perform an orbit or path recovery
of said spacecraft or said aircraft;

measuring the useful phase difference comprising either a correlation of the signals received respectively on the first receiving
antenna and the second receiving antenna with a reference target signal, or the analysis of the signals received respectively
on the first receiving antenna and the second receiving antenna using a Fast Fourier Transform (FFT) or Phase-Locked Loop
(PLL);

transmitting a calibration signal to the receiving base via a transmitting antenna;
measuring a calibration phase difference between signals corresponding to the calibration signal received respectively on
the first receiving antenna and the second receiving antenna; and

compensating variations of the calibration phase difference measurements on the useful phase difference measurements.

US Pat. No. 9,859,619

SEGMENTED STRUCTURE, IN PARTICULAR FOR A SATELLITE ANTENNA REFLECTOR, WITH COMBINED ROTATION AND TRANSLATION DEPLOYMENT DEVICE

AIRBUS DEFENCE AND SPACE ...

1. Segmented structure, in particular for a satellite antenna reflector, said segmented structure comprising:
at least two panels, intended to be deployed in space, a first panel referred to as the main panel, comprising a front face
and a rear face, and a second panel referred to as the secondary panel, also comprising a front face and a rear face; and

at least one deployment device connected to the respective rear faces of said main and secondary panels and is configured
to bring said secondary panel into one or the other of the following two positions, relative to said main panel;

a storage position, in which said secondary panel is positioned at least in part on said main panel on the rear face thereof,
the front face of said secondary panel being directed in the same direction as the front face of said main panel; and

a deployed position, in which said secondary panel is positioned towards the outside of the main panel, to the side and against
said main panel in order to form a continuous assembly at least on the front faces thereof,

wherein said deployment device comprises:
a translation system comprising at least one translation unit provided with a helical geared motor, said translation system
being connected to said secondary panel and being configured to generate a translational movement of said secondary panel
relative to said main panel; and

a rotation system configured to cause said translation system and the secondary panel connected to said translation system
to rotate relative to said main panel, said rotation system comprising at least one rotation unit configured to generate a
rotation between a first structural element rigidly connected to the rear face of the main panel and a second structural element,
to which the translation system is connected.

US Pat. No. 9,331,775

METHOD AND SYSTEM FOR DETECTING BROADCAST SIGNALS TRANSMITTED BY TERRESTRIAL SOURCES AND RECEIVED BY A SATELLITE

AIRBUS DEFENCE AND SPACE ...

1. A method for detecting broadcast signals, transmitted by terrestrial sources and received by a satellite, in individual
signals respectively from different individual antennas of an antenna array of the satellite, wherein:
said method comprises a first detection iteration and a second detection iteration, each of said first and second detection
iterations comprising a step of forming, from the individual signals, virtual beams of different respective main radiation
directions, and a step of searching for the presence of broadcast signals in the virtual beams,

for at least one broadcast signal detected during the first detection iteration, the respective contributions of said at least
one detected broadcast signal to the different individual signals are attenuated, relative to said first detection iteration,
for all or part of the virtual beams formed during the second detection iteration.

US Pat. No. 9,239,225

FOURIER-TRANSFORM INTERFEROMETER WITH SELF-APODIZATION COMPENSATION

Airbus Defence and Space ...

1. An interferometer comprising:
a splitting plate, adapted to split an initial radiation beam into two secondary beams;
two optical arms equipped with reflecting surfaces effective for the secondary beams, each arm being intended for one of the
secondary beams and being in outward-return form between the splitting plate and the reflecting surface of said arm, the reflecting
surfaces being oriented in order to superimpose from the splitting plate, the two secondary beams originating from the respective
arms in an output beam;

in a first one of the optical arms: a variable-thickness system comprising two mobile prisms called respectively internal
and external, the external prism having an external face constituting the reflecting surface of the first optical arm;

in a second one of the optical arms: a mirror constituting the reflecting surface of said second optical arm, and a compensation
assembly adapted so that respective optical thicknesses of said compensation assembly and of the variable-thickness system
of the first optical arm are equal when an optical path length difference between the two optical arms is zero;

a mobile system adapted to displace the internal and external prisms along directions that are opposite and parallel to facing
surfaces of the prisms, so as to modify simultaneously an optical path length of the first optical arm and the thickness of
the variable-thickness system;

an output optical arm comprising a detector arranged to receive the output beam, and produce a signal representing an intensity
of said output beam; and

a calculation unit, adapted to calculate a Fourier transform of the signal produced by the detector, as a function of a parameter
representing the difference in length of the optical path between the two arms;
characterized in that the mobile system has a single degree of freedom of movement and itself comprises:
at least one pair of levers having identical lengths within one and same pair, rotatably hinged about respective points that
are fixed with respect to the splitting plate along respective main axes parallel to each other within the pair of levers,
by means of rotating connexions, each with one single axis; and

two support elements each borne by the two levers of one and the same pair by means of additional rotating connexions, each
with one single axis parallel to the main axes of said pair of levers; and

an actuation system, adapted to cause a rotation of the levers so that each support element is displaced while remaining parallel
to itself when the actuation system is activated;
the internal and external prisms are respectively borne by the two support elements; anda ratio between respective displacement lengths of the internal and external prisms is constant and set by distances between
the fixed points and the additional rotating connexions, so that the mobile system simultaneously produces a variation of
the optical path length difference between the two optical arms and a self-apodization compensation of an interferogram resulting
from the signal produced by the detector when the actuation system is activated.

US Pat. No. 9,517,590

DEVICE FOR EXPELLING/CONTAINING LIQUIDS FOR A SPACECRAFT TANK

AIRBUS DEFENCE AND SPACE ...

1. A device for expelling/retaining a predetermined liquid and suitable for integration in a liquid tank operable at low or
zero gravity, the device comprising:
a peripheral zone;
a liquid expulsion/retention zone;
a single three-dimensional structure comprising a set of wire elements spaced apart from one another and extending between
the peripheral zone and the liquid expulsion/retention zone, and a set of spacers intersecting and linking the wire elements
together to form a lattice;

wherein the wire elements are substantially oriented in a direction of flow of the liquid within the device, the liquid being
retained between the wire elements by capillarity;

wherein, for at least part of a surface orthogonal to the wire elements, intersections of the wire elements with an orthogonal
surface are points determining sides of polygons forming a paving of the orthogonal surface; and

wherein the wire elements are linked together by spacers comprising projections, parallel to a direction of the wire elements,
on the surface orthogonal to the wire elements merged with the sides of the polygons.

US Pat. No. 10,032,386

METHOD FOR CARRYING OUT A REAL SITUATION SIMULATION TEST INCLUDING GENERATION OF VARIOUS VIRTUAL CONTEXTS

Airbus Defence and Space ...

1. A method for implementing a test simulating a real situation and comprising the steps:generating a first simulation context comprising a first display of:
a first portion of a first virtual environment defined over 360° on a semi-hemispherical screen, said portion being projected over a first angle of less than 300°;
an avatar representing a first user in simulation, the avatar being generated at an emulated GPS position of the first user in the virtual environment;
activating a generation of a second simulation context comprising:
retrieving the position of the head and its orientation from a first capture device positioned on a helmet worn by the first user in simulation,
generating a second refreshed portion of the first virtual environment computed according to the position and orientation of the captured head,
displaying said second portion on an optical unit integrated in the helmet,
the first and second portions coinciding over an angle corresponding to that of the second portion for at least one position and one orientation of the predefined head.

US Pat. No. 9,887,512

THICK DISC LASER AMPLIFICATION SYSTEM AND USES THEREOF

COMPAGNIE INDUSTRIELLE DE...

1. Laser amplification system, of the type comprising:
a plurality of amplifier discs, each of the amplifier discs having a first face which is reflective at wavelengths both of
a laser beam and of a pumping beam, the saturation flux of an active medium of the amplifier discs being less than or equal
to 3 J·c-?2, wherein the amplifier discs are all arranged in a same plane on a support which is shared by the amplifier discs; and

at least one semiconductor-type pumping device, generating the pumping beam for the amplifier discs, wherein each of the amplifier
discs is a thick amplifier disc;

the laser amplification system further comprises at least one heat dissipation element, to which the first face of the amplifier
discs is rigidly connected; and

the laser amplification system is configured so that an optical path of a pulsed-type laser beam between two amplifier discs
is less than fifteen times the diameter of an amplifier disc, wherein the system is configured to generate a circulation of
the laser beam which passes from a first amplifier disc to a second adjacent amplifier disc by reflecting from a surface which
both allows the laser beam to be reflected and allows the pumping beam to be transmitted, wherein the surface includes a single
dichroic mirror which is shared by all the amplifier discs.

US Pat. No. 9,846,243

METHOD FOR CALIBRATING SPATIAL ERRORS, AND METHOD AND SYSTEM FOR ESTIMATING THE ATTITUDE OF A VEHICLE

AIRBUS DEFENCE AND SPACE ...

1. A method for of estimating attitude of a craft as a function of measurements of phase differences of radio-electric signals
received by at least three non-aligned reception antennas of the craft, comprising steps of:
calibrating spatial errors induced by phase biases affecting measurements of the phase differences of the radio-electric signals
received by said at least three non-aligned reception antennas of the craft, said phase biases depending on a direction of
incidence of the radio-electric signals with respect to the craft, comprising steps of:

obtaining respective positions of the craft and a pair of satellites situated at a given instant in a radio-electric field
of view of the craft;

calculating by at least one processor, an inter-satellite angular distance of said pair of satellites as a function of the
respective positions of the craft and said pair of satellites to obtain a theoretical inter-satellite angular distance;

calculating by said at least one processor, respective directions of incidence of said pair of satellites with respect to
the craft as a function of phase measurements of radio-electric signals received from said pair of satellites by the three
non-aligned reception antennas of the craft;

calculating by said at least one processor, the inter-satellite angular distance of said pair of satellites as a function
of the respective directions of incidence of said pair of satellites with respect to the craft to obtain an estimated inter-satellite
angular distance; and

calculating by said at least one processor, the spatial errors for the respective directions of incidence of the said pair
of satellites with respect to the craft as a function of the theoretical inter-satellite angular distance and of the estimated
inter-satellite angular distance determined for said pair of satellites; and

compensating the spatial errors calculated during a calculation of the attitude of the craft.

US Pat. No. 9,461,733

DEVICE AND METHOD FOR OPTIMIZING THE GROUND COVERAGE OF A HYBRID SPACE SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. A telecommunications system for intermittent data transfer from and to at least one user located substantially on the surface
of a celestial body, the telecommunications system comprising:
at least one surface transmitter/receiver terminal associated with each user;
one or more moving signal repeaters to repeat signals transmitted to or received from the surface terminals, the repeaters
moving above the surface of the celestial body, each moving repeater having at least one antenna oriented toward the surface
of the celestial body, and configured to allow communications from and to surface terminals, each antenna producing a transmission/reception
beam, a track of which on the surface of the celestial body forms a ground track, the progressive sweeping of the surface
by the ground track forms a strip called a swath; and

an active track length reduction device, configured to ensure that, at each point P of the swath of the moving repeater, and
on each pass of the latter, a total coverage time along a line of movement by at least one active antenna of the moving repeater
determines a length Lac(P) called the active communication length, whose mean value Lac over a width of the swath is smaller than the width lf of said swath along an axis perpendicular to the line of movement.

US Pat. No. 9,077,428

HYBRID SPACE SYSTEM BASED ON A CONSTELLATION OF LOW-ORBIT SATELLITES WORKING AS SPACE REPEATERS FOR IMPROVING THE TRANSMISSION AND RECEPTION OF GEOSTATIONARY SIGNALS

AIRBUS DEFENCE AND SPACE ...

1. Telecommunications system, intended for low-throughput data transfer between at least two users located substantially on
the surface of a celestial body, comprising:
at least two transmitting/receiving surface terminals, each associated with a different user,
one or more stationary means GEO above the surface of the celestial body, these stationary means being able to transmit data
from and to a predefined coverage area with a line of sight to the stationary means, and

one or more signal repeater to repeat signals transmitted and/or received from the stationary means GEO and the surface terminals,
said repeater traveling above the surface of the celestial body and comprising means of performing an amplification without
frequency translation of the signal received from the stationary means GEO; a same frequency band being used for communications
between the surface terminals and the repeater and for communications between the repeater and the stationary means; and wherein
at least one user terminal utilizes a CDMA type interface to manage arrival of two signals bearing Doppler and delay differences.

US Pat. No. 9,825,371

SEGMENTED STRUCTURE, PARTICULARLY FOR SATELLITE ANTENNA REFLECTOR, PROVIDED WITH AT LEAST ONE STRIP-COMPRISING UNFURLING DEVICE

Airbus Defence and Space ...

1. A segmented structure, in particular for a satellite antenna reflector, said segmented structure comprising:
at least two panels, a first so-called main panel comprising a front face and a rear face, and a second so-called secondary
panel also comprising a front face and a rear face; and

at least one deployment device connected to the rear faces respectively of said main and secondary panels and configured to
bring said secondary panel into one or other of the following two positions, relative to said main panel:

a storage position, in which said secondary panel is at least partly superimposed on said main panel on the rear face thereof,
the front face of said secondary panel being directed in the same direction as the front face of said main panel; and

a deployed position, in which said secondary panel is positioned towards the outside of the main panel, alongside and against
said main panel so as to form a continuous assembly at least on their front faces,

wherein said deployment device comprises:
at least one strip, said strip being fixed by a first of its ends to the secondary panel at a so-called contact face thereof,
which comes into contact with a so-called contact face of the main panel in the deployed position, and being connected to
the main panel at the contact face thereof, said strip:

having a flexibility allowing the strip to be folded at least at so-called hinge regions in the storage position;
being resiliently prestressed in the storage position so as to unwind automatically and autonomously, when the movement between
the secondary panel and the main panel is released, so as to move the secondary panel during the unwinding until the strip
reaches a substantially rectilinear unwound position, and

self-locking in the unwound position, and
at least one reel device that is configured to reel up said strip from its unwound position, a reeling of the strip bringing
the secondary panel towards the main panel.

US Pat. No. 9,462,595

METHOD FOR IDENTIFYING REUSABLE MULTIPLEXING RESOURCES AND TELECOMMUNICATIONS SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. A method for identifying uplink multiplexing resources of a multi-beam satellite that can be used in a terrestrial telecommunications
system by a transmitting station to transmit radio-electric signals to a receiving station, comprising the steps of:
estimating a maximum interference level authorized with respect to the satellite for an uplink multiplexing resource for radio-electric
signals transmitted from a zone of coverage, wherein the transmitting station or the receiving station is a base station having
a range delimiting the zone of coverage in which the transmitting station is situated, and wherein different beams of satellite
use different uplink multiplexing resources;

estimating a radiation power of the radio-electric signals transmitted by the transmitting station;
measuring, by the transmitting station, a real reception level of the radio-electric signals transmitted by the satellite;
determining a potential level of interference of the transmitting station as a function of the real reception level measured
and of the estimated radiation power of the transmitting station; and

determining whether said uplink multiplexing resource is usable by the transmitting station by comparing the potential level
of interference of the transmitting station with the maximum interference level authorized for said uplink multiplexing resource.

US Pat. No. 9,225,467

METHOD FOR CALIBRATING THRESHOLDS AND THRESHOLD CALIBRATION MODULE FOR A SATELLITE TELECOMMUNICATIONS SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. A method, carried out by one or both of a transmitting device and a receiving device, for updating a threshold used for
selecting a transmission format from a plurality of transmission formats associated with said threshold, a selected transmission
format to be used by a transmitting device of a satellite telecommunications system to transmit data packets to the receiving
device over a radio-frequency propagation channel, the transmission format associated to said threshold being selected when
an estimated value of an instantaneous channel quality is higher than said threshold, said method comprising:
updating a table associating a plurality of transmission statistics to respective values of the instantaneous channel quality,
said transmission statistics of the table being representative of an amount of estimated errors for a plurality of data packets,
said table being updated from estimated errors in data packets that are received by the receiving device via the transmission
format associated with the threshold to be updated; and

from values of the instantaneous channel quality estimated during reception of said data packets received by the receiving
device, updating the threshold to be, according to the updated table, a value of the instantaneous channel quality enabling
a predefined value of the transmission statistics to be provided,

wherein a satellite of the satellite telecommunications system is in a geostationary orbit, and the transmission statistics
of the table are anticipated transmission statistics, and

wherein each anticipated transmission statistic, associated to a given value of the instantaneous channel quality, being an
expected transmission statistic for data packets that will be received, relative to a point in time when said given value
of the instantaneous channel quality was estimated, after expiry of a period of time representative of the time period between
a point in time when the instantaneous channel quality is estimated and a point in time when the transmission format, selected
according to said estimated value of the instantaneous channel quality, is presented and applied to the receiving device.

US Pat. No. 9,065,530

CALIBRATION METHOD AND SYSTEM FOR ESTIMATING A PATH DIFFERENCE OF A TARGET SIGNAL TRANSMITTED BY A SPACECRAFT OR AIRCRAFT

AIRBUS DEFENCE AND SPACE ...

1. A method for estimating a path-length difference between two paths followed by a target signal transmitted by a spacecraft
or aircraft respectively to a first receiving antenna and a second receiving antenna of a receiving base, the method comprising
the steps of:
measuring a useful phase difference between signals corresponding to the target signal received respectively on the first
receiving antenna and the second receiving antenna;

estimating the path-length difference as a function of the useful phase difference measurements;
transmitting a calibration signal to the receiving base via a transmitting antenna;
measuring a calibration phase difference between signals corresponding to the calibration signal received respectively on
the first receiving antenna and the second receiving antenna;

compensating variations of the calibration phase difference measurements on the useful phase difference measurements; and
measuring calibration phase difference comprising either a correlation of the signals received respectively on the first receiving
antenna and the second receiving antenna with the transmitted calibration signal, or an analysis of the signals received respectively
on the first receiving antenna and the second receiving antenna using a Fast Fourier Transform (FFT) or Phase-Locked Loop
(PLL).

US Pat. No. 9,847,829

SATELLITE COMMUNICATION SYSTEM, LEO SATELLITE RELAYING COMMUNICATIONS BETWEEN A GEO SATELLITE AND TERRESTRIAL STATIONS, THE UPLINKS AND DOWNLINKS USING THE SAME FREQUENCY BAND AND TIME-DIVISION MULTIPLEXING

AIRBUS DEFENCE AND SPACE ...

1. A payload for a repeater satellite in a telecommunication system, said repeater satellite being on a traveling orbit above
the surface of Earth, and the payload being configured to repeat data received from a stationary satellite above the surface
of Earth to terminals that are substantially on the surface of Earth, and to repeat data received from the terminals to the
stationary satellite, wherein said payload comprises:
a first circuitry configured to use a same frequency band for repeating data to the stationary satellite, referred to as uplink
transmissions, and for repeating data to the terminals, referred to as downlink transmissions, said frequency band being any
one of the bands VHF, UHF, L, S, C, X, Ka or Q; and

a second circuitry configured to time multiplex the uplink transmissions and the downlink transmissions, such that said payload
does not perform uplink transmissions to the stationary satellite during intervals of time in which said payload performs
downlink transmissions to the terminals, and such that said payload does not perform downlink transmissions to the terminals
during intervals of time in which said payload performs uplink transmissions to the stationary satellite.

US Pat. No. 9,554,065

IMAGE CAPTURE WITH ADDITION OF ACCUMULATION SIGNALS FOR ADJACENT PHOTODETECTORS

Airbus Defence and Space ...

1. An image capture instrument, comprising:
an image formation optics, suitable for forming an image of a scene in a focal plane from a radiation originating from said
scene, the image formation optics having a pupil of diameter D and a focal length f determining a numerical aperture N and
a spatial cut-off frequency fC effective for patterns in the image, according to the formula:

N=f/D and fC=1/(N·?),

where ? is a wavelength of the radiation;
a row of photodetectors situated in the focal plane, with a pitch p of the photodetectors which is constant along the row;
and

a controller suitable for controlling readings of accumulation signals produced respectively by the photodetectors,the controller defining a series of segments within the row, which each comprise one same number of adjacent photodetectors,
called a segment length, and for controlling the readings of the accumulation signals by adding together said accumulation
signals for photodetectors which belong to one and the same segment,the controller further defining the segments so that an offset length M between two successive segments in the row, expressed
as a number of photodetectors, is constant along the row, and greater than 1/(2·fC·p),wherein the instrument being characterized in that the segment length is greater than the offset length M, and less than twice
said offset length M.

US Pat. No. 10,072,915

METHOD AND DEVICE FOR CONNECTING AND SEPARATING TWO ELEMENTS, WITH CONNECTING PLATES

Airbus Defence and Space ...

1. A device for connecting and separating a first element and a second element, the device comprising:a first connecting plate attached to the first element and a second connecting plate attached to the second element, wherein the first connecting plate has a first connecting surface on a first side and a thermal surface on a second side opposite to the first side, wherein the thermal surface faces the first element, and wherein the second connecting plate has a second connecting surface facing the first connecting surface;
a connecting layer comprising solder or glue placed between the first and second connecting surfaces so as to define a local connection of the first element to the second element;
thermite, placed on the thermal surface, close to the connecting layer; and
an electrical control configured to remotely pyrotechnically trigger the thermite, to securely separate the first element from the second element by a warming-up.

US Pat. No. 9,625,216

HEAT TRANSFER SYSTEM TWO SEPARATE HEAT LOOPS IN EXCHANGE

Airbus Defence and Space ...

1. A heat transfer system comprising at least one main capillary pumped diphasic fluid loop and a secondary capillary pumped
diphasic fluid loop; the main fluid loop and the secondary fluid loop cooling at least one hot source, the main fluid loop
including at least:
a main evaporator evaporating a main cooling fluid by recovering heat from said hot source; wherein the main evaporator includes
a capillary structure;

a main vapour pipe conveying the main cooling fluid in the vapour state from the main evaporator to a main condenser;
the main condenser condensing the main cooling fluid by conveying heat to a first cold source; and
a main liquid pipe conveying the main cooling fluid in the liquid state from the main condenser to the main evaporator;
the secondary fluid loop including at least:
a secondary evaporator evaporating a secondary cooling fluid by recovering heat from said hot source; wherein the secondary
evaporator includes a secondary capillary structure;

a secondary vapour pipe conveying the secondary cooling fluid in the vapour state from the secondary evaporator to a secondary
condenser;

the secondary condenser condensing the secondary cooling fluid by conveying heat to a second cold source; and
a secondary liquid pipe conveying the secondary cooling fluid in the liquid state from the secondary condenser to the secondary
evaporator;

the main cooling fluid of the main fluid loop is in heat exchange with the secondary cooling fluid in the liquid state of
the secondary fluid loop, wherein the main cooling fluid being distinct from the secondary cooling fluid and the main fluid
loop being separate from the secondary fluid loop.

US Pat. No. 9,506,972

SYSTEM AND METHOD FOR DETECTING AND LOCATING AN INSULATION FLAW IN A SOLAR GENERATOR ON A SPACE VEHICLE

AIRBUS DEFENCE AND SPACE ...

1. A system for detecting and locating an insulation flaw, comprising:
a solar generator on a spacecraft comprising a plurality of flaps, each flap bearing at least one solar cell and being connected
to a first electrical line by a first load and to a second electrical line by a second load, said at least one solar cell
is connected to an electrical distribution network and said at least one solar cell is electrically insulated from said each
flap such that current flows in the first and second electrical lines in response to an insulation flaw;

an evaluation component to evaluate currents flowing in the first electrical line and the second electrical line, respectively;
a detector to detect the insulation flaw in the solar generator based on evaluations of the currents flowing in at least one
of the first electrical line and the second electrical line;

wherein a ratio of impedances of the first load and of the second load of a flap is denoted as an impedance ratio of the flap;
wherein the solar generator comprises at least two flaps exhibiting different respective impedance ratios; and
wherein the detector is configured to locate the detected insulation flaw by comparing the evaluations of the currents flowing
respectively in the first and second electrical lines with the respective impedance ratios of said at least two flaps.

US Pat. No. 9,317,907

METHOD AND SYSTEM FOR CORRECTING A DIGITAL IMAGE BY GEOMETRIC ADJUSTMENT OF THIS IMAGE ONTO A REFERENCE IMAGE

AIRBUS DEFENCE AND SPACE ...

1. A method for correcting a digital image to be corrected stored on a client device by a geometric adjustment of the digital
image to be corrected onto a reference image stored on a server device connected to the client device by a communication network,
wherein the method includes:
obtaining, by the server device, at least one area of interest of the reference image,
sending, to the client device information representative of each area of interest,
obtaining, by the client device, at least one image part respectively delimited by each received area of interest, each image
part being either a part of the digital image to be corrected or a part of an image resulting from the digital image to be
corrected,

sending, to the server device, each obtained image part,
determining, by the server device, parameters of a correction to apply to the digital image to be corrected, said parameters
being determined by geometric adjustment of at least one said image part onto the reference image,

sending, to the client device, the determined parameters, and
applying, by the client device, the correction to the digital image to be corrected, said correction using the received parameters
and a ground elevation model corresponding to the image to be corrected.

US Pat. No. 9,180,983

ACTUATOR WITH TRANSFER OF ANGULAR MOMENTUM FOR THE ATTITUDE CONTROL OF A SPACECRAFT

Airbus Defence And Space ...

1. An attitude control actuator, to be fixed in a spacecraft with respect to a reference system linked to the spacecraft,
the actuator comprising:
a first momentum wheel;
at least one motor arranged to drive in rotation said first momentum wheel about an axis of rotation of said first momentum
wheel; and

a second momentum wheel arranged to rotate about an axis parallel to or coinciding with the axis of rotation of the first
momentum wheel,

wherein the second momentum wheel is mechanically coupled with the first momentum wheel through a mechanical coupling means
comprising a variable rotation speed drive, said mechanical coupling means imposing a negative ratio (R), of a rotation speed
of the second momentum wheel to a rotation speed of the first momentum wheel, resulting in contra-rotating first and second
momentum wheels, said ratio (R) being continuously modifiable between a minimum value and a maximum value by transferring
kinetic energy from one wheel to the other wheel when the first and second momentum wheels are rotating by the coupling means
in response to a command.

US Pat. No. 10,086,482

METHOD OF MANUFACTURING A PIECE COMPRISING SEVERAL PARTS CONNECTED TOGETHER

AIRBUS DEFENCE AND SPACE ...

1. A method of manufacturing a final piece including several materials, the method comprising:inserting an elastomer in at least one insertion cavity of an initial piece so that the elastomer is in contact and fixed with the initial piece; and
after inserting the elastomer in the at least one insertion cavity, cutting the initial piece in at least two distinct parts so that the at least two distinct parts are fixed together but are not in contact with each other, the at least two distinct parts being connected to each other by the elastomer,
wherein the final piece includes at least one clearance cavity arranged to, once the initial piece is cut, allow a movement of the two distinct parts relative to each other by deformation of the elastomer.

US Pat. No. 9,988,162

METHOD AND DEVICE FOR CONTROL OF A SUNLIGHT ACQUISITION PHASE OF A SPACECRAFT

AIRBUS DEFENCE AND SPACE ...

1. A method for controlling a phase of acquisition of the sun by a spacecraft with a nonzero angular momentum of an axis DH, the spacecraft comprises a body, a solar generator and a drive mechanism to drive the solar generator in rotation about an axis Y, the method comprising the steps of:controlling actuators of the spacecraft to place the spacecraft in an intermediate orientation with respect to the angular momentum, in which the axis Y is substantially orthogonal to the axis DH of the angular momentum;
controlling the drive mechanism of the solar generator, at least partially deployed beforehand, to orientate the solar generator toward the sun;
after the spacecraft has been placed in the intermediate orientation and after the solar generator has been oriented toward the sun, the method further comprises the steps of:
controlling the actuators of the spacecraft to reduce the angular momentum of the spacecraft; and
controlling the actuators of the spacecraft to place the spacecraft in an acquisition orientation with respect to the sun, in which the axis Y is substantially orthogonal to the direction of the sun with respect to the spacecraft.

US Pat. No. 9,709,658

METHOD AND SYSTEM FOR MONITORING A PHASE FOR TRANSFERRING A SATELLITE FROM AN INITIAL ORBIT TO A MISSION ORBIT

Airbus Defence and Space ...

1. A method for monitoring a transfer phase wherein a satellite transfers from an initial Earth orbit to a mission Earth orbit
different from said initial Earth orbit using electric propulsion, comprising:
using a ground array antenna, the ground array antenna comprising a plurality of elementary antennas, said elementary antennas
arranged such to be non-coplanar with each other, and each elementary antenna having a main radiation lobe with a width greater
than or equal to 20° to estimate a direction of said satellite during said transfer phase, said elementary antennas being
oriented such that respective fields of vision of each one of the plurality of elementary antennas overlap,

wherein the estimating of the direction of said satellite includes the steps of
receiving, on a pair of said elementary antennas, signals corresponding to a target signal transmitted by the satellite during
the transfer phase, and

performing, via a processor device in communication with said ground array antenna, at least one measurement of a useful phase
difference between the received signals corresponding to the target signal.

US Pat. No. 9,108,750

MODULAR DEVICE FOR MULTI-AXIAL INSULATION AGAINST VIBRATION AND IMPACTS, BASED ON ELASTOMER

Airbus Defence and Space ...

1. A device for a multi-axis insulation of at least one item of equipment that generates vibrations on board a carrying structure,
comprising at least three insulation modules distributed on the periphery of said item of vibrating equipment or of a support
of said item, each insulation module comprising at least two rigid parts at least one of which, called outer part is designed
to be attached to said carrying structure, and of which at least one other, called inner part, is designed to be attached
to said item of vibrating equipment or to said support, said inner part extending along a radial axis, at least one inner
part and at least one outer part being connected to one another by at least one elastomer insulation pad attenuating by deformation
of said at least one insulation pad the transmission of low-amplitude vibrations generated by said item of equipment, each
module also comprising at least two flexible abutments mounted on at least one inner part or on at least one outer part, and
each abutment having a free end facing another part, respectively outer part or inner part, and with no contact with said
other part at rest, each of said at least two flexible abutments acting on at least one axis of deformation of said at least
one insulation pad and two of said flexible abutments, called longitudinal abutments, being active on longitudinal axis perpendicular
to the radial axis, in opposite directions, wherein each insulation module also comprises two other flexible abutments, called
tangential abutments, that are active along a tangential axis perpendicular to the radial axis and to the longitudinal axis,
in opposite directions along the tangential axis.

US Pat. No. 9,926,087

SATELLITE COMPRISING ELECTRICAL PROPULSION MEANS, METHOD FOR PLACING SUCH A SATELLITE IN A STATION AND METHOD FOR KEEPING SAID SATELLITE IN ITS STATION

Airbus Defence and Space ...

1. A satellite configured to be stationed in a mission orbit around a celestial body, comprising:an Earth face configured to be disposed facing the Earth when the satellite is on a station and an opposite anti-Earth face, the satellite defining a satellite frame of reference centered on a center of mass of the satellite and the satellite frame of reference comprising three axes X, Y and Z, the axis Z configured to be directed towards the Earth when the satellite is on the station;
a propulsion device comprising a first electrical thruster of orientable thrust direction and a second electrical thruster of orientable thrust direction;
at least two electrical-thruster power units and an electrically interconnecting network connecting a first electrical-thruster power unit to the first electrical thruster of orientable thrust direction and connecting a second electrical-thruster power unit to the second electrical thruster of orientable thrust direction;
wherein the propulsion device further comprises an electrical thruster of fixed orientation relative to the satellite, the electric thruster of fixed orientation having a thrust line aligned with an axis Z and passing through the center of mass of the satellite; and
wherein the electrically interconnecting network connects each electrical-thruster power unit to the electrical thruster of fixed orientation so that each electrical-thruster power unit is configured to supply power to either an associated electrical thruster of orientable thrust direction or the electrical thruster of fixed orientation.

US Pat. No. 9,413,990

IMAGING METHOD

Airbus Defence and Space ...

1. An imaging method for providing a final image composed of intensity values assigned respectively to pixels of a matrix
of the final image consisting of adjacent columns and adjacent rows of pixels, the method comprising:
carrying an image-capturing instrument on board an aircraft or spacecraft, said image-capturing instrument comprising an image-sensing
optical system and at least one array of photodetectors which is arranged in a focal plane of the image-sensing optical system,
said array of photodetectors consisting of adjacent columns and adjacent rows of photodetectors;

using the image-capturing instrument to capture radiation intensity values originating from unit regions of a scene; then
constructing the final image by assigning certain of the intensity values to the pixels of the final image matrix,
wherein:
the captured intensity values are restricted to a selection of one photodetector out of two along the columns and along the
rows of the array of photodetectors, in a manner that constructs a selection of one photodetector out of four in said array
of photodetectors; and

the pixels of the final image matrix to which are assigned the intensity values captured by the selected photodetectors are
adjacent to each other in the columns and rows of said final image matrix, and

wherein the resolution in the focal plane of the image-sensing optical system which results from the size of each photo detector
is two times smaller than the resolution associated with each pixel in the final image.

US Pat. No. 9,234,561

VIBRATION ISOLATING DEVICE

AIRBUS DEFENCE AND SPACE ...

1. A vibration isolation device designed to be positioned between a structure (10) and an equipment anchor plate (11), said device comprising:
a lattice made of isolation bars, with each isolation bar comprising at least one axial actuator (25),

the lattice being an active hexapod comprising six identical isolation bars (12) positioned according to a regular geometry,

the isolation six bars (12) being arranged such that the control of tension-compression forces in each of the six isolation bars (12) makes force and torque control of six separate degrees of freedom at an interface between the structure and the equipment,
so as to produce effective isolation along all six degrees of freedom,

wherein at least one end-fitting of each isolation bar consists of an elastomeric element (16) made of elastomeric material, wherein each actuator is an actively-controllable piezoelectric translator, thereby the six
actuators being actively-controllable on all six degrees of freedom,

in combination with the structure (10) and the equipment anchor plate (11), wherein,

each end of each isolation bar includes the elastomeric element,
each elastomeric element is an elastomeric block that provides a passive filtering function within a predefined frequency
band, and

a first elastomeric block of each isolation bar is attached to an upper supporting block and a second elastomeric block of
each isolation bar is attached to a lower supporting block, the lower blocks being positioned on a lower first circle on the
structure, and the upper blocks being positioned on a second circle on the equipment anchor plate, the upper blocks being
angularly offset in relation to the lower blocks.

US Pat. No. 9,910,058

METHOD AND DEVICE FOR MEASURING THE ANGLE OF ATTACK AND THE SIDESLIP OF AN AIRCRAFT

AIRBUS DEFENCE AND SPACE ...

1. Method for measuring the angle of attack of the longitudinal axis of an aircraft with respect to the relative wind, in
which method a probe is used which is provided, at the front end thereof, with a central directional sensor which is arranged
at the intersection of the horizontal and vertical midplanes of said probe, and with at least two eccentric midplane directional
sensors which are in parallel with said central directional sensor and are arranged at an equal distance therefrom on either
side of said horizontal midplane of said probe, the method comprising:
pivotally connecting said probe to said aircraft about a first pivot axis which is in parallel with said horizontal midplane
of said probe and is orthogonal to said longitudinal axis of the aircraft;

rotating said probe about said first pivot axis in order to make said probe assume the particular inclined position in which
the measurements provided by said eccentric midplane directional sensors are equal; and

measuring the particular angle of inclination which is produced, in this particular inclined position, between said horizontal
midplane of the probe and the longitudinal axis (L-L) of the aircraft,

wherein said probe is provided, at the front end thereof and in addition to said central directional sensor and said eccentric
midplane directional sensors, with at least two lateral directional sensors which are in parallel with said central directional
sensor and are arranged at an equal distance therefrom on either side of said vertical midplane of said probe, and wherein,
in order to measure the sideslip of the aircraft, the method comprises:

pivotally connecting said probe to said aircraft about a second pivot axis which is in parallel with said longitudinal axis
of the aircraft;

rotating said probe and said first pivot axis about said second pivot axis in order make said probe assume the particular
combined inclined position in which not only are the measurements provided by said eccentric midplane directional sensors
equal, but so too are the measurements provided by said lateral directional sensors; and

measuring the particular value of the angle of rotation of said second pivot axis in said particular combined inclined position
of the probe.

US Pat. No. 9,625,182

COOLING DEVICE

AAIRBUS DEFENCE AND SPACE...

1. A cooling device for cooling at least two separate heat sources, further comprising:
a closed circuit in which a diphasic fluid flows;
a single capillary evaporator configured to produce a pumping pressure and in thermal contact with a primary heat source which
is one of the heat sources;

a heat exchanger in thermal contact with a secondary heat source to be cooled and not producing any pumping pressure;
at least one first condenser positioned downstream of the capillary evaporator and upstream of the heat exchanger;
at least one last condenser positioned upstream of the capillary evaporator and downstream of the heat exchanger;
wherein the heat exchanger and the condensers are dimensioned such that head losses in the circuit are less than a maximum
capillary pressure of the capillary evaporator; and wherein a pressure of the diphasic fluid in the closed circuit continuously
decreases from a capillary evaporator exit during an operation of the cooling device.

US Pat. No. 9,143,689

STABILIZATION OF A LINE OF SIGHT OF AN ON-BOARD SATELLITE IMAGING SYSTEM

Airbus Defence and Space ...

1. Method for stabilizing a line of sight of an imaging system on-board a satellite, said imaging system comprising:
a telescope arranged to form an image of a scene in a focal plane, according to the line of sight of the imaging system; and
at least one matrix image sensor arranged in the focal plane and suitable for capturing successive images in a sequential
mode, in which photodetectors of the sensor are successively and individually controlled during an accumulation phase of a
detection signal for received radiation, followed by a read phase of an accumulated signal, based on an order for scanning
the photodetectors that is repeated in a continuous loop, each repetition of scan of the photodetectors corresponding to a
newly captured image, and the read phase for any of the photodetectors being carried out at the same time as the accumulation
phase for other ones of the photodetectors;
wherein, for several windows, each of which consists of a different subset of adjacent photodetectors within the sensor, each
window being smaller than a total use surface of the sensor, an image portion captured in one of the windows during one of
the repetitions of the scan of the photodetectors is compared with a reference image content for the same window, so as to
characterize a variation of the line of sight between said repetition of the scan of photodetectors and a reference scan,
and a new characterization of the variation of the line of sight being obtained separately for each window at each repetition
of the scan of the photodetectors;and wherein an orientation of at least part of the imaging system is changed so as to modify the line of sight to compensate,
at least partially, for the variation of said line of sight.

US Pat. No. 9,055,240

POLYCHROMATIC IMAGING METHOD

Airbus Defence and Space ...

1. A polychromatic imaging method in the spectral band of 360 nm to 950 nm used for observation, comprising the following
steps:
carrying an image-sensing optical system on board an aircraft or spacecraft, said image-sensing optical system comprising
a telescope and being adapted to form views, in at least one focal plane, respectively based on radiation within several spectral
sub-bands each contained within the observation spectral band;

placing at least one array of photodetectors in said at least one focal plane, in order to capture an intermediate image of
each view formed by the image-sensing optical system at a resolution associated with said intermediate image;

respectively capturing the intermediate images of a same scene for each spectral sub-band; and
merging the intermediate images respectively captured for the spectral sub-bands, in order to form a final polychromatic image,
the telescope of the image-sensing optical system determining a pupil which is common to the spectral sub-bands, and a dimension
of said common pupil setting a spatial cutoff frequency which is different for each spectral sub-band,

the spectral sub-bands comprising a first spectral sub-band and at least one other spectral sub-band extending towards long
wavelengths, with said other spectral sub-band extending towards the long wavelengths having at least one wavelength greater
than an upper limit of said first spectral sub-band, the pupil of the telescope being sized such that the spatial cutoff frequency
for the first spectral sub-band is greater than a Nyquist frequency of the intermediate image captured for said first spectral
sub-band,

the method being characterized by the pupil of the telescope additionally being sized so that the spatial cutoff frequency,
for said other spectral sub-band extending towards the long wavelengths, is less than the Nyquist frequency of the intermediate
image captured for said first spectral sub-band.

US Pat. No. 10,050,439

DEVICE FOR THE ELECTRIC POWER SUPPLY OF A LOAD AND ASSOCIATED METHOD

AIRBUS GROUP SAS, Blagna...

1. A device for the electric power supply (10) of a load (11), said device comprising:at least first and second energy storage elements (13, 14) connected to said load (11), said first and second energy storage elements (13, 14) comprising a maximum specified discharge current (Ibat.max) and a minimum specified voltage (Vbat.min) guaranteeing a life of said first and second energy storage elements (13, 14);
a first converter (30) connected to the first energy storage element (13) to define a power (Pbat(t)) delivered by the first energy storage element (13);
a second converter (31) connected to the second energy storage element (14) to define a power (Psc(t)) delivered by the second energy storage element (14);
a calculation body (19) having a first input, a second input, a third input connected to the load (11), a first output connected to control the first converter (30), and a second output connected to control the second converter (31);
a first monitor (16) connected to the first input of the calculation body, the first monitor providing, via the first input, information about a maximum instantaneous power (Pbat.max(t)) that can be requested of said first energy storage element (13), said first monitor (16) further providing information about an electromotive force (Ebat(t)) and a resistance (Rbat(t)) of a Thévenin equivalent model of said first energy storage element (13) reflecting an internal state and a state of health of said first energy storage element (13); and
a second monitor (17) connected to the second input of the calculation body, the second monitor providing, via the second input, information about a maximum instantaneous power (Pbat.max(t)) that can be requested of said second energy storage element (14), said second monitor (17) further providing information about an electromotive force (Ebat(t)) and a resistance (Rbat(t)) of a Thévenin equivalent model of said second energy storage element (14) reflecting an internal state and a state of health of said second energy storage element (14),
wherein the calculation body:
i) determines power needs (Pchg(t)) of said load (11),
ii) determines, for each of the first and second energy storage elements(13, 14), a maximum secured power (Pbat.max.spec(t)) according to the electromotive force (Ebat(t)) and to the resistance (Rbat(t)), according to the maximum specified current (Ibat.max) and to the minimum specified voltage (Vbat.min), and
iii) controls (Cbat(t), Csc(t)) respectively the first and second converters (30, 31) for controlling each of the first and second energy storage elements (13, 14) to define the power (Pbat(t), Psc(t)) respectively delivered by said first and second energy storage elements (13, 14), and
wherein said control (Cbat(t), Csc(t)) are adjusted over time (t) according to the power needs (Pchg(t)) of said load (11) and to the maximum secured power (Pbat.max.spec(t)) of each energy storage element (13, 14).

US Pat. No. 9,902,507

ARTIFICIAL SATELLITE AND METHOD FOR FILLING A TANK OF PROPELLENT GAS OF SAID ARTIFICIAL SATELLITE

AIRBUS DEFENCE AND SPACE ...

1. Artificial satellite (2) having a longitudinal axis (A-A) that extends in the launch direction, said artificial satellite (2) comprising:—a mounting structure (14) supporting equipment-bearing walls (4, 8, 6, 10, 12),—a launcher-adapter (16) rigidly connected to the mounting structure (14),—a first radiator (26),—at least one first system (42) for transporting heat by a fluid comprising at least one first heat-exchange section (50) and a second heat-exchange section (52), said second heat-exchange section (52) in thermal contact with said first radiator (26), wherein said first heat-exchange section (50) is in thermal contact with at least one portion of the launcher-adapter (16) to allow for heat exchanges between the launcher-adapter (16) and the first radiator (26).

US Pat. No. 9,516,544

METHOD FOR MANAGING SERVICE POLICY IN A TELECOMMUNICATIONS NETWORK

AIRBUS DEFENCE AND SPACE ...

1. A telecommunication network, said network comprising a first security domain, called black domain, comprising at least
one radio link, at least one second domain with higher security, called red domain, connected to the black domain,
said telecommunication network including:
a first predefined list of profiles, each profile of the first predefined list containing a set of parameters applicable to
the management of the service policy for the black domain, the profiles of the first predefined list being adapted to respective
congestion levels on the radio link;

a second predefined list of profiles, each profile of the second predefined list containing a set of parameters applicable
to the management of the service policy for each red domain, the profiles of the second predefined list being adapted to respective
congestion levels on the radio link;

said first and second predefined lists being predefined so that a service policy profile correspond to a detected congestion
level, for all domains and in a consistent manner between the domains, the parameters of the profiles of the first and second
predefined lists being defined according to the topology of the black domain,

wherein, once the first and second predefined list of profiles are established in their respective domains, the black domain
is configured for:

performing a first detection of congestion level on the radio link in the black domain;
selecting a first profile among the profiles of the first predefined list, the first profile being adapted to the congestion
level of the radio link detected in the black domain;

and wherein, once the first and second predefined list of profiles are established in their respective domains, each red domain
is configured for:

performing a second detection of congestion level on the radio link in said red domain, said second detection being based
solely on exchanges of messages in said red domain; and

selecting a second profile among the profiles of the second predefined list established in said red domain, the second profile
being adapted to the congestion level of the radio link detected in said red domain.

US Pat. No. 9,135,716

METHOD FOR ESTIMATING THE MOVEMENT OF A TRAVELING OBSERVATION INSTRUMENT FLYING OVER A CELESTIAL BODY

AIRBUS DEFENCE AND SPACE ...

1. A method for estimating the movement of an observation instrument on-board a vehicle flying over a celestial body, the
observation instrument comprising at least two strips with different lines of sight, each strip realizing the acquisition
of successive image lines making up a composite image, by scanning its line of sight over the celestial body, parts of the
composite images representing substantially a same scene of the celestial body, wherein the estimated movement is determined
by searching a movement hypothesis that optimizes a global function, the value of the global function, obtained for a given
movement hypothesis, cumulating the respective values of an image similarity function and of an external similarity function
calculated for said given movement hypothesis:
the value of said image similarity function corresponds to a similarity between values of matched pixels of at least a pair
of composite images, matched pixels being pixels that represent, theoretically, the same point of the observed scene, given
said given movement hypothesis, and

the value of said external similarity function corresponds to a similarity between said given movement hypothesis and measurements
of the observation instrument's movements, made by one or several sensors different from the observation instrument's strips,

the method comprising, for calculating the value of the image similarity function for each movement hypothesis considered
during the optimization of the global function, the following steps:

determining, for the at least one pair of composite images, at least one spatio-temporal transformation using the considered
movement hypothesis and a geometric model of the observation instrument; and

matching the pixels of the at least one pair of composite images using the at least one spatio-temporal transformation.

US Pat. No. 9,945,356

ASSEMBLY OF SECTIONS OF STRUCTURAL PARTS

AIRBUS DEFENCE AND SPACE ...

1. A wing or blade in at least two sections facing each other, each section comprising a longitudinal bearing structure provided with at least one sole piece, the longitudinal bearing structure of each section comprising a longitudinal member perpendicular to the sole piece; wherein a link between the sections comprises at least one first link plate linking an end of the sole piece of each section facing each other; and wherein a slot is arranged between the longitudinal member and the sole piece of each section facing each other by reducing a height of the longitudinal member in a part receiving the first link plate, the first link plate linking the sole pieces being received in said slot.

US Pat. No. 9,840,342

DEVICE FOR SENSING AND CAPTURING A SPACE OBJECT, INCLUDING A PRESSURE ELEMENT AND AT LEAST TWO RECLOSABLE ELEMENTS

AIRBUS DEFENCE AND SPACE ...

1. An orbital device for capturing a space object, comprising:
a pressure element configured to come into direct mechanical contact with the space object to be captured,
a support,
at least two reclosable elements free to move between an open position for capturing the the space object and a closed position
for retaining the space object,

an apparatus configured to mechanically transmit movement from the pressure element to each reclosable element, the mechanical
transmission apparatus being configured to entrain each reclosable element in displacement between the open position and the
closed position by pressure of the space object on the pressure element, the mechanical transmission apparatus comprising:

at least one support bar on which the pressure element is located, the support bar being configured to move the pressure element
in translation relative to the support,

at least one connecting rod mechanically connecting the pressure element to one of the reclosable elements,
at least one hinge located between the support and the at least two reclosable elements, the at least one connecting rod making
the reclosable element pivot about the hinge during the translation displacement of the pressure element relative to the support,
and

a blocking member in the closed position of at least one of the reclosable elements, the blocking member preventing subsequent
displacement of the reclosable element from the closed position against a mechanical energy stored during closing of the reclosable
element.

US Pat. No. 9,726,248

VIBRATION ISOLATION MODULE HAVING REDUCED NONLINEAR EFFECTS

Airbus Defence and Space ...

1. An isolation module between a satellite launcher, which is a vibration-generating device, and a satellite structure to
be isolated, the isolation module comprising:
at least two fastening parts intended to be fastened respectively on the vibration-generating device and the structure to
be isolated,

an elastomeric connecting means interposed between the two fastening parts, allowing at least one degree of freedom in translation
along a longitudinal axis between the two fastening parts,

wherein a first fastening part, comprises a frame that includes;
two lower branches, one within the continuous extension of the other,
two upper branches one within the continuous extension of the other; and
a longitudinal branch extending in the longitudinal plane of symmetry, the frame forming an H,
the two upper branches and two lower branches of the frame being symmetrical with each other with respect to a plane perpendicular
to the longitudinal axis,

wherein a second fastening part, comprises a support, the support includes;
two aligned median branches, one extending toward the other without meeting, the support forming a C,
wherein each of the support median branches extend between two branches of the frame,
the frame and the support each have a longitudinal plane of symmetry perpendicular to the radial axis, and in which,
the elastomeric connecting means comprise at least one pair of identical elastomer pads, in which each pad extends along the
longitudinal axis between a first end and a second end, a first pad having the first end supported on a lower branch of the
frame and the second end supported on the median branch of the support and the second pad having the first end supported on
the upper branch of the frame and the second end supported on the median branch of the support, the two pads of the pair being
thus mounted in parallel between the frame and the support and being active along the longitudinal axis in opposite directions,
so that when one pad works under tension, the other pad of the pair works under compression, and vice-versa, a stiffness of
the module being symmetrical, whether a force applied thereto along the longitudinal axis is oriented in one direction or
the opposite direction, and
each pad is dimensioned so that a contact surface S1 of one end in contact with a radial branch and a free contact surface S2 satisfy the relationship:

US Pat. No. 10,050,654

METHOD AND SYSTEM FOR SUPPRESSING A PARASITE SIGNAL RECEIVED BY A SATELLITE PAYLOAD

AIRBUS DEFENCE AND SPACE ...

1. A method of suppressing a parasite signal received with a useful signal by an array of elementary antennas of a payload of a satellite, the parasite signal and the useful signal being transmitted respectively by a terrestrial parasite transmitter and a terrestrial useful transmitter, comprising steps of:analog formation by the payload of analog beams from elementary signals supplied by said array of elementary antennas by an analog beam forming network, the analog formation step comprising:
analog formation of at least one useful analog beam in which a gain of the array of elementary antennas in a direction of arrival of the useful signal is higher than a gain in a direction of arrival of the parasite signal; and
analog formation of at least one auxiliary analog beam in which the gain of the array of elementary antennas in the direction of arrival of the parasite signal is higher than the gain in the direction of arrival of the useful signal;
digitization by the payload of said at least one auxiliary analog beam and of said at least one useful analog beam to respectively provide a digitized auxiliary analog beam and a digitized useful analog beam; and
digital formation by the payload of a digital beam by combining the digitized auxiliary analog beam favoring reception of the parasite signal and the digitized useful analog beam favoring reception of the useful signal, said combination using weighting coefficients determined in order to suppress the parasite signal in said digital beam.

US Pat. No. 10,017,279

SPACE VEHICLE COMPRISING POSTS FOR FORMING A STACK, STACK COMPRISING AT LEAST TWO SUCH VEHICLES PLACED IN A LAUNCHER, AND METHOD FOR RELEASING THE VEHICLES

AIRBUS DEFENCE AND SPACE ...

1. A spacecraft (1, 100) intended to be put into orbit around a planet, the spacecraft (1, 100) comprising:at least one equipment carrying module (2, 102), for supporting the spacecraft (1, 100) equipment;
at least three posts (12, 112) extending at least partially in a same longitudinal direction (A) and at the periphery of the equipment carrying module (2, 102), each post (12, 112) being provided with at least one releasable locking device (15, 115) which may have two states:
a locked state, wherein the locking device (15, 115) is attached to an additional locking device (15, 115),
an unlocked state, wherein the locking device (15, 115) is released from any other locking device (15, 115);
a reinforcing structure (16, 116) which rigidly connects each post (12, 112) transversely to at least two other posts (12, 112).

US Pat. No. 10,097,461

METHOD AND DEVICE FOR DETECTING CONGESTION ON A TRANSMISSION LINK

AIRBUS DEFENCE AND SPACE ...

1. A method for detecting congestion on a transmission link, the transmission link having two ends, one or more items of equipment being connected to each end of said transmission link so that at least one of said ends has only one item of equipment connected thereto, the method comprising:determining a master and one or more slaves among the items of equipment connected to the ends of the transmission link, the master always being the item of equipment that is solely connected at one of the ends of the transmission link;
exchanging data via said transmission link during a predetermined period;
calculating, by each item of equipment, in application layer of said item of equipment, a data rate of data sent or received during the predetermined period via said transmission link;
exchanging, at initiative of the master and at the end of the predetermined period, messages between the master to the at least one slave, so that at least one of the items of equipment gathers the data rates calculated by the master and by the at least one slave for the predetermined period, and wherein the exchanged messages are messages in application layer;
determining, in application layer of the at least one of the items of equipment that gathers the data rates calculated by the master and by the at least one slave for the predetermined period, that a congestion occurs, when the data rate of data received at one of the ends of the transmission link is less than the data rate of data sent at the other end of the transmission link, wherein information representative of the data rate of data received or sent at one of the ends of the transmission link are included in the exchanged messages; and
informing a quality of service management system, when a congestion occurrence via the transmission link has been determined, that said congestion has occurred, so that service admission at boundaries of a quality of service domain be adapted to the congestion occurrence,
and further comprising:
sending an acknowledgement message acknowledging, by the master, each response received, wherein the acknowledgement message is a message in application layer,
calculating a round trip time, when successive responses are received by the master; and
predicting that congestion occurs, when a gradual extension of the round trip appears between the successive response, wherein the gradual extension appears when the calculated round trip time continuously increases along the successive responses.

US Pat. No. 9,617,015

METHOD OF COMMANDING AN ATTITUDE CONTROL SYSTEM AND ATTITUDE CONTROL SYSTEM OF A SPACE VEHICLE

AIRBUS DEFENCE AND SPACE ...

1. A method for controlling an attitude control system (30) of a space vehicle (10) where the attitude control system has a maneuvering first subsystem that includes at least one reaction wheel, comprising:
controlling an attitude of the space vehicle (10) during at least one preparation phase; and

following said controlling, performing an observation phase during which an image capture is performed;
wherein the at least one preparation phase comprises the following sub-steps:
a preparation step (50), during which commands are issued to the maneuvering first subsystem in order to control the attitude of the space vehicle
(10) such that the attitude of said space vehicle is tilted from one observation attitude to another, and

following said preparation step, a step (55) in which the at least one reaction wheel is stopped after the wheel has started moving, during which the speed of rotation
of the at least one reaction wheel is set to a substantially zero value prior to each observation phase,

wherein, during the observation phase, commands are issued to a fine control second subsystem (310) that further controls the attitude of the space vehicle (10), said fine control second subsystem comprising at least one actuator and having a lower vibration signature than that of
the maneuvering first subsystem, and

wherein the preparation phase and the observation phase are recurring phases.

US Pat. No. 9,937,658

LINK BETWEEN A THIN METAL LINER AND A COMPOSITE WALL BY THERMOPLASTIC PARTICLE-FILLED COATING

AIRBUS DEFENCE AND SPACE ...

1. A process for providing the assembly between a first structural element made from a first material and a second structural element made from a thermoplastic matrix composite material, comprising the following steps:a first step of preparing a coating, said coating consisting of an epoxide resin, wherein a powder of particles of a thermoplastic material is incorporated;
a second step of coating, during which the coating is applied to the surface of the first structural element;
a third step during which the coating is polymerized;
a fourth step, during which the first structural element covered with its coating is welded to the second structural element to which it must be assembled.

US Pat. No. 10,046,868

DEVICE FOR CONTROLLING THE SPEED OF A SPACEPLANE DURING THE TRANSITION FROM A PHASE OF SPACE FLIGHT TO A PHASE OF AERONAUTICAL FLIGHT AND ASSOCIATED TRANSITION METHOD

AIRBUS DEFENCE AND SPACE ...

1. A space aircraft suited to aeronautical flight, comprising a body and a first wing structure defining a lift-generating surface and attitude-control means, where said control means comprise one or more flaps positioned under the lift-generating surface and that can be maneuvered between a retracted position and an inclined, deployed, aerodynamic-braking position during the transition of the craft from a phase of space flight to a phase of aeronautical flight, and wherein the one or more flaps comprise a first axis of maneuvering for opening the one or more flaps against incoming airstream, and a second axis of maneuvering for opening the flap or flaps parallel to incoming airstream.

US Pat. No. 9,957,919

ANAEROBIC HYBRID PROPULSION DEVICE WITH FUEL PRESENT IN THE FORM OF DIVIDED SOLIDS

AIRBUS DEFENCE AND SPACE ...

13. An anaerobic propulsion device of a hybrid type, the device comprising a segregation device arranged between a reservoir of granules of fuel in a solid form and a combustion chamber; the segregation device is configured to prevent the granules of the fuel in the solid form from passing between the reservoir and the combustion chamber, the segregation device comprises orifices to allow a passage of the fuel that has become pasty, liquid or vaporized; the reservoir comprises a pressure device to apply pressure to the granules to push the granules toward the segregation device, the pressure device comprises a deformable membrane arranged at a surface of the reservoir of the granules, and wherein the reservoir further comprises a set of radial dividers which are perpendicular to a surface of the segregation device, each of the radial dividers having a geometry with a capillary gradient to encourage the supply of the fuel in a paste or liquid form to the segregation device.

US Pat. No. 9,592,922

SATELLITE SUPPORT STRUCTURE COMPRISING A DAMPING CONNECTING DEVICE

AIRBUS DEFENCE AND SPACE ...

1. A satellite comprising a satellite support structure to support at least one device of said satellite, said satellite support
structure comprising:
a frame having at least one flat angle bracket, the flat angle bracket including first and second wings defining an angle
therebetween, each wing having a first and second side;

at least one panel being connected to one wing of said at least one flat angle bracket by a damping connector;
the damping connector comprising:
a first counter-plate located adjacent the at least one panel,
a first elastomer layer between the first counter-plate and the first side of one wing of the flat angle bracket,
a second elastomer layer located adjacent the second side of the one wing of the flat angle bracket,
a second counter-plate arranged against the second elastomer layer, wherein each of the first and second counter-plates and
first and second elastomer layers include through openings to allow the passage of a fixing device.

US Pat. No. 9,776,740

AIRCRAFT CAPABLE OF PASSING FROM THE AERIAL DOMAIN TO THE SPATIAL DOMAIN AND METHOD FOR AUTOMATICALLY ADAPTING THE CONFIGURATION OF SAME

AIRBUS DEFENCE AND SPACE ...

1. A method for automatically adapting the configuration of an aircraft, the mission of which makes it change over from air
flight to space flight,
said aircraft comprising a single deck provided with at least one manned cabin and further comprising:
aerobic propulsion means and steerable anaerobic propulsion means,
aerodynamic piloting surfaces,
a system configured to control the environment of the cabin, supplied by the aerobic propulsion means,
a store of breathable survival gas (10A), which store is configured to temporarily supply said manned cabin with breathable gas in the event of said system configured
to control the environment of the cabin malfunctioning at high altitude,

an electrical power supply system which is configured to be actuated by said aerobic propulsion means,
electrical energy storage means, and
a system configured to produce piloting commands,
wherein the method comprises:
installing an additional store of breathable gas on-board said aircraft, which store is configured to supply said system configured
to control the environment of the manned cabin,

determining, prior to said mission, the conditions required at the end of the air flight in order to change over to the space
flight, and

detecting said conditions during the air flight, and, when they are achieved:
supplying the system configured to control the environment of the cabin by means of the additional supply of breathable gas
in place of the aerobic propulsion means,

verifying that the environment of the cabin resulting from being supplied by the additional store of breathable gas is correct
and then, if this is the case,

powering the electrical power supply system via the electrical energy storage means in place of the aerobic propulsion means,
verifying that the electrical power produced by said electrical power supply system powered by said electrical energy storage
means is correct and then, if this is the case, and

transmitting piloting commands generated by said system configured to produce piloting commands to the steerable anaerobic
propulsion means in place of said aerodynamic piloting surfaces.

US Pat. No. 10,144,534

SPACECRAFT

AIRBUS DEFENCE AND SPACE ...

1. Spacecraft (1, 75) comprising:a housing (2) defining an inner space (11) and an outer space (13), the housing (2) having a first surface (7) and a second surface (8) opposite the first surface (7),
a first radiator (16) and a second radiator (18) supported by the first surface (7) and respectively the second surface (8), the first radiator (16) and the second radiator (18) each comprising a main inner surface (15, 21), a main outer surface (17, 23) opposite the main inner surface (15, 21) and side surfaces (19, 25), wherein
the spacecraft (1) further comprises a first auxiliary radiator (32) and a first auxiliary heat-transfer device (34, 76) thermally connecting said first auxiliary radiator (32) to the main inner surface (21) of the second radiator (18), the first auxiliary radiator (32) being arranged in a first portion (46) of the outer space (13), said first portion (46) being defined by the main outer surface (17) of the first radiator and by the first planes (48, 50, 52, 54) containing the side surfaces (19) of the first radiator.

US Pat. No. 10,511,639

STRUCTURE FOR INTEGRATING MOBILE SERVICES

AIRBUS DEFENCE AND SPACE ...

1. A method comprising, for each access network of a plurality of available networks to which a terminal connects:a step, where the terminal initiates a connection to one of the plurality of available networks;
a step, where the terminal proceeds to its authentication to said one of the plurality of available networks;
a step, where the terminal initiates security parameters for the connection to said one of the plurality of available networks;
a step, where the terminal is registered by a structure for integrating mobile services via the plurality of available networks, and
wherein a treatment of service requests received by an application server and emitted by applications of terminals is managed by a control room, the control room being connected to said structure for integrating mobile services, said treatment of service requests comprising for each request of service received from a recipient application of a terminal towards a source application:
a step, where the structure for integrating mobile services receives a request of service from the application server,
a step, where the structure for integrating mobile services controls access of said service for a recipient user provided with the terminal,
a step, where the structure for integrating mobile services determines whether said user simultaneously accesses to several simultaneously operating services, said structure for integrating mobile services carrying out a hierarchy depending on a priority level assigned to each service for using the simultaneously operating services for said same user according to the priority levels assigned to the applications,
a step, where the structure for integrating mobile services determines for all the available networks, which one(s) is/are the most suitable to provide the requested service as a function of at least a network load, of a unicast or broadcast configuration, and of the load balancing between the networks,
a step, where the structure for integrating mobile services implements the service on the selected network(s),
a step, where the structure for integrating mobile services initiates a session between the source application towards the recipient application on the user terminal for which the service is intended,
a step, where the structure for integrating mobile services enables media streams to be ready to be sent by the source application towards the recipient application.

US Pat. No. 9,828,116

SPACECRAFT

AIRBUS DEFENCE AND SPACE ...

1. A spacecraft comprising:
a body having a face +Y and a face ?Y opposite the face +Y;
a first radiator carried by at least one face out of the face +Y and the face ?Y; said first radiator having an outer face;
a first supporting arm extending substantially perpendicularly to the outer face of the first radiator, said first supporting
arm having a longitudinal axis;

a drive motor suitable for rotating the first supporting arm about said longitudinal axis of the first supporting arm, the
speed of rotation of the first supporting arm being substantially equal to the speed of revolution of the sun around the spacecraft;

a first assembly carried by the first supporting arm, said first assembly having at least one absorption face suitable for
absorbing a portion of the incident solar radiation during the vernal and autumnal equinoxes, said first assembly being suitable
for transmitting heat generated by said portion of the incident solar radiation absorbed to the first radiator; said absorption
face being inclined with respect to the outer face of the first radiator by an angle substantially between 20° and 26°,
wherein said first assembly comprises at least two slats attached one above the other and separated from each other by a free
space, said at least two slats being stationary with respect to the first supporting arm.

US Pat. No. 9,749,980

SYSTEM AND METHOD FOR MANAGING COMMUNICATIONS OF AT LEAST ONE TERMINAL IN A COMMUNICATION NETWORK

AIRBUS DEFENCE AND SPACE ...

1. A terminal for use in a communications network, said terminal being configured to transmit, during a phase of registering
the terminal in said communications network, an identifier of subscription to a communication service implemented in said
communications network, wherein said terminal implements in software form by execution of a set of instructions by a machine
or a programmable circuit or implements in hardware form by a dedicated machine or component or implements by a Subscriber
Identity Module SIM card inserted in the terminal via a SIM card reader of said terminal:
dynamically changing the identifier of subscription to said communication service by obtaining a new subscription identifier
from a server via the communications network; and

re-registering with said communications network with the new subscription identifier,
wherein when said terminal uses the new subscription identifier to communicate with another terminal of the communications
network, said terminal transmits a request, to the server via the communications network, for obtaining a call identifier
attributed to said other terminal, said call identifier enabling calling said other terminal via the communications network,
the other terminal being registered with said communications network with a respective identifier of subscription to the communication
service,

wherein said terminal is further configured to receive from the server, in response to said request, the call identifier attributed
to said other terminal,

and wherein said terminal is further configured to further communicate with said other terminal using the call identifier
that is attributed to said other terminal and received from the server in response to said request.

US Pat. No. 10,392,133

METHOD FOR PLANNING THE ACQUISITION OF IMAGES OF AREAS OF THE EARTH BY A SPACECRAFT

AIRBUS DEFENCE AND SPACE ...

1. A method for planning an acquisition of images of terrestrial areas Z1, . . . , ZN by a spacecraft on a mission around the Earth following a predetermined traveling orbit, each terrestrial area Zi being associated with a request Ri of priority pi such that the terrestrial area Zi corresponds to a visual accessibility time period Ti along said predetermined traveling orbit, comprising following successive steps:determining, for each period Ti, discrete acquisition opportunities for the terrestrial area Zi such that a start date included in said period Ti, a duration of execution, a kinematic local constraint and a weight are associated with each discrete acquisition opportunity;
grouping together the discrete acquisition opportunities of the terrestrial area Zi into a set D;
ranking the discrete acquisition opportunities of the set D, the discrete acquisition opportunities being ranked in order of increasing start date and denoted by Di;
evaluating a kinematic compatibility between the discrete acquisition opportunities of the set D, taken pairwise according to their respective rankings; and
determining an optimum sequence of discrete acquisition opportunities having a maximum weight, and being kinematically compatible.

US Pat. No. 10,232,959

METHOD AND SYSTEM FOR CONTROLLING THE ORBIT OF A SATELLITE IN EARTH ORBIT

AIRBUS DEFENCE AND SPACE ...

1. A method for controlling an orbit of a satellite on station in an Earth orbit, the satellite comprising an angular momentum device, a propulsion system comprising at least one thruster and a satellite frame of reference centered on a center of mass of the satellite, the satellite frame of reference includes three axes X, Y and Z, the axis X is parallel to a speed vector of the satellite, the axis Z is directed toward the Earth, and the axis Y is orthogonal to the axes X and Z, the method comprises steps of:determining an inclination control requirement for the orbit of the satellite;
determining a longitude control requirement for the orbit of the satellite;
determining an angular momentum unload requirement for the angular momentum storage device of the satellite;
determining a maneuver plan comprising at least two orbit control maneuvers with respective thrust forces of the propulsion system having respective thrust directions that are not parallel in an inertial frame of reference;
determining the thrust forces as a function of the inclination control requirement, of the longitude control requirement and of the angular momentum unload requirement, wherein the thrust forces of said at least two orbit control maneuvers are determined to control simultaneously an inclination and a longitude of the orbit of the satellite while producing torques configured to unload the angular momentum storage device of the satellite in respective planes that are not parallel in the inertial frame of reference, so that said at least two orbit control maneuvers of the maneuver plan unloads the angular momentum storage device about the three axes;
controlling simultaneously the inclination and the longitude of the orbit of the satellite and an angular momentum stored in the angular momentum storage device by commanding the propulsion system and a transporter of the propulsion system to apply the thrust forces of said at least two orbit control maneuvers of the maneuver plan;
wherein the transporter is commanded to:
modify angles between a thrust direction of said at least one thruster and the axes X, Y of the satellite frame of reference, respectively;
move said at least one thruster while maintaining a constant thrust direction in the satellite frame of reference to produce a torque about any axis in a plane orthogonal to said thrust direction.

US Pat. No. 9,929,796

VIRTUAL POLAR SATELLITE GROUND STATION FOR LOW ORBIT EARTH OBSERVATION SATELLITES BASED ON A GEOSTATIONARY SATELLITE POINTING AN ANTENNA OVER AN EARTH POLE

Airbus Defence and Space ...

1. A satellite system comprising:a first satellite operating in a first orbit around the Earth; and
a second satellite operating in second orbit around the Earth,
wherein the first satellite includes a fixed beam pointed for an indefinite period of time to a zone, which is calculated to be above and tangential to the Earth's surface, and through which zone the second satellite passes,
wherein the fixed beam does not move in order to maintain communication with the second satellite,
wherein the first satellite is configured to maintain said communication without tracking the second satellite while the second satellite passes through the zone, and wherein the first satellite points one fixed beam at least temporarily to a zone of a super-polar space above the Earth's North Pole or to a zone of a super-polar space above the Earth's South Pole or simultaneously a first fixed beam at least temporarily to zones of a super-polar space above the Earth's North Pole and a second fixed beam at least temporarily to zones of a super-polar space above the Earth's South Pole.

US Pat. No. 10,136,357

METHOD FOR MANAGING CONGESTION OF A TRANSMISSION LINK IN A PACKET COMMUNICATION NETWORK

Airbus Defence and Space ...

1. A method for managing congestion on a transmission link from a first item of network equipment to a second item of network equipment in a packet communication network, wherein the first item of network equipment is associated with a first congestion detection application and the second item of network equipment is associated with a second congestion detection application, and wherein the second congestion detection application implements, conjointly with the first congestion detection application, a congestion control mechanism per class of service on a transmission link in which the second congestion detection application performs, for at least one class of service, the method comprising:receiving, for each class of service, a first control message coming from the first congestion detection application, the first control message including information representing a first volume of data colored by the class of service and transmitted by the first item of network equipment up to a first instant;
receiving, for each class of service, a second control message coming from the first congestion detection application, the second control message including information representing a second volume of data colored by the class of service and transmitted by the first item of network equipment up to a second instant;
determining a first divergence between the first volume of data and the second volume of data;
on reception of each first control message, obtaining information representing a third volume of data colored by the class of service and received by the second item of network equipment via the transmission link up to a third instant;
on reception of each second control message, obtaining information representing a fourth volume of data colored by the class of service and received by the second item of network equipment via the transmission link up to a fourth instant;
determining, for each class of service, a second divergence between the third volume of data and the fourth volume of data; and
generating or not, for each class of service, an alarm signal representing congestion on the transmission link of the data colored by the class of service, according to a difference between the first divergence and the second divergence for the class of service.

US Pat. No. 10,393,546

DEVICE AND METHOD FOR DETERMINING THE ATTITUDE OF A SATELLITE, AND SATELLITE CARRYING SUCH A DEVICE

Airbus Defence And Space ...

1. A device to restore an attitude of a satellite provided with an attitude control system comprising at least one inertial actuator comprising a rotary element mounted to rotate about an axis of rotation, the device comprising:an angular sensor to measure an angle of rotation of the rotary element about its axis of rotation;
a processor comprising at least one Kalman filter that receives positional measurements of the angle of rotation of the rotary element as input;
wherein said at least one Kalman filter determines the attitude or the attitude variation of the satellite, induced by the rotation of the rotary element, as a function of said positional measurements of the angle of rotation of the rotary element by the angular sensor without considering a speed of rotation of the rotary element; and
the rotation of the rotary element being controlled to generate an attitude control torque to restore the attitude of the satellite based on the determined attitude or attitude variation of the satellite.

US Pat. No. 10,676,218

SPACECRAFT

AIRBUS DEFENCE AND SPACE ...

1. A spacecraft comprising a body having at least one face, at least one radiator carried by said face and at least one thermal insulation device carried by the radiator, said thermal insulation device comprising:a first screen device able to cover a first area of said radiator, said first screen device comprising a thermally insulating and flexible sheet and
a traction device able to pull in a pulling direction so that the insulating sheet covers the first area in a mode referred to as deployed mode,
wherein said thermal insulation device comprises further at least two springs able to generate a constant reaction force, said springs being preformed so as to roll onto themselves at rest, said springs being fixed to the insulating sheet, said springs each having a first end fixed to the traction device and a second end (44) fixed to the radiator; and
wherein the traction device is configured to pull in said pulling direction on the first end of said springs of the first screen device so that the insulating sheet covers said first area in said deployed mode, said traction device being able to release the first end of said springs so that the insulating sheet exposes the first area to the space environment in a mode referred to as exposure mode.

US Pat. No. 10,630,093

METHOD FOR OPTIMISING THE ARCHITECTURE OF THE POWER SUPPLY OF A LOAD

AIRBUS GROUP SAS, Blagna...

1. A method for optimizing the architecture of an electric power supply of a load, comprising:determining a dimensioning mission profile according to a capacity demand over time of a load;
defining possible energy storage sources for hybridization, among energy storage sources of the battery, super-capacitor or fuel cell type;
associating a characteristic behavior model with each energy storage source;
determining couples of energy storage sources which are capable of generating a mission profile with minimum mass;
determining, among potential couples of energy storage sources, a couple with the lowest mass; and
constructing an electric power supply of a load using said couple with the lowest mass.

US Pat. No. 10,536,378

METHOD AND DEVICE FOR DETECTING CONGESTION ON A TRANSMISSION LINK

AIRBUS DEFENCE AND SPACE ...

1. A method for detecting congestion on a transmission link, the transmission link having two ends, one or more items of equipment being connected to each end of said transmission link so that at least one of said ends has only one item of equipment connected thereto, the method comprising:determining a master and one or more slaves among the items of equipment connected to the ends of the transmission link, the master always being the item of equipment that is solely connected at one of the ends of the transmission link;
performing exchanges of data between the master and the one or more slaves via said transmission link during a predetermined period;
calculating, by the master and the one or more slaves, in application layer of said master and one or more slaves, a data rate of data sent or received during the exchanges of data performed in the predetermined period via said transmission link;
gathering, in application layer of the master or of the one or more slaves, the calculated data rates, wherein information representative of the calculated data rate of data received or sent at one of the ends of the transmission link is included in messages exchanged between the master and at least one of the slaves;
comparing the gathered data rates and determining therefrom, in application layer of the item of equipment that gathers the data rates, whether the data rate of data received at one of the ends of the transmission link is less than the data rate of data sent at the other end of the transmission link; and
determining, in application layer of the item of equipment that gathers the data rates, that a congestion occurs, when the item of equipment that gathers the data rates determines that the data rate of data received at one of the ends of the transmission link is less than the data rate of data sent at the other end of the transmission link.

US Pat. No. 10,184,766

METHOD AND DEVICE FOR CONNECTING AND SEPARATING TWO ELEMENTS, WITH COMBINED CONNECTING AND SEPARATING MEANS

AIRBUS DEFENCE AND SPACE ...

2. A device for connecting and separating a first element and a second element, wherein the first element has a first surface and the second element has a second surface in a face-to-face relationship with the first surface, the device comprising:a first connecting plate attached to the first element, such that the first connecting plate has an outer face in direct contact with the first surface of the first element, and the first connecting plate has a first connecting face opposite the outer face of the first connecting plate,
a second connecting plate attached to the second element, such that the second connecting plate has an outer face in direct contact with the second surface of the second element, and the second connecting plate has a second connecting face opposite the outer face of the second connecting plate and in a face-to-face relationship with the first connecting face,
a connecting arrangement comprising a thermite and a connecting agent arranged between the face-to-face relationship of the first and second connecting faces, in direct contact with the first and second connecting faces, such that the connecting arrangement defines a local connection between the first element and the second element, and
an electrical control arranged to remotely pyrotechnically trigger the thermite in the connecting arrangement to cause a warming of the thermite, wherein only the warming of the thermite causes a warming-up and a destruction of the local connection between the first element and the second element without an explosion, and wherein the second surface is not mechanically deformed during the destruction of the local connection.

US Pat. No. 10,659,159

COMBINED IMAGING AND LASER COMMUNICATION SYSTEM

Airbus Defence and Space ...

3. A combined system for imaging and communication by laser signals comprising:a telescope comprising at least a primary mirror, a secondary mirror and a tertiary mirror, and the telescope is adapted for forming, in a focal plane of said telescope, an image of a scene located in a pointing direction of the telescope by reflection of radiation received from the scene at least on the primary mirror, then on the secondary mirror and then on the tertiary mirror; and
an image sensor arranged in the focal plane of the telescope and configured to capture the image of the scene;
a source of laser radiation configured to produce laser radiation which includes laser transmission signals;
a frame in a satellite configured for operation in outer space and supporting the source of laser radiation, the image sensor and the telescope, wherein the telescope is affixed to the frame so that a pointing direction of the telescope is fixed with respect to the frame;
a focal plane duplication element arranged to create an image of the focal plane of the telescope which forms a secondary focal plane, and
the combined system being arranged so that the laser radiation which constitutes the laser transmission signals is brought to the secondary focal plane at a location of said secondary focal plane which is optically superimposed on the image sensor by the focal plane duplication element, and so that the laser radiation of the laser transmission signals, produced by the source of laser radiation, is directed by said focal plane duplication element toward the tertiary mirror, then successively reflected by said tertiary mirror, then by the secondary mirror, then by the primary mirror, in order to be emitted towards a communication receiver external to the combined system.

US Pat. No. 10,565,715

METHOD OF ESTIMATING THE MOTION OF A CARRIER WITH RESPECT TO AN ENVIRONMENT AND CALCULATION DEVICE FOR NAVIGATION SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. A method for estimating a motion of a carrier with respect to an environment in relation to which the carrier is moving, the carrier bearing on board at least one navigation sensor and at least one vision sensor producing images of the environment, the method comprising the steps, performed by a calculation device, of:identifying, in the images acquired by said at least one vision sensor, characteristic elements of the images representing characteristic elements of the environment;
calculating at least one condensed measurement as a function of the characteristic elements of at least two images acquired at different times, said at least one condensed measurement being representative of characteristics of the motion of the carrier during acquisition of said at least two images;
estimating the motion of the carrier by a navigation filter performed as a function of navigation measurements performed by said at least one navigation sensor and as a function of said at least one condensed measurement;
wherein said at least one condensed measurement is calculated as a function furthermore of an a priori estimation of the motion of the carrier provided by the navigation filter; and
estimating an error made in said at least one condensed measurement; estimating a relation between an error made in the a priori estimation of the motion of the carrier and the error made in said at least one condensed measurement; and wherein the navigation filter estimates the motion of the carrier as a function furthermore of the error made in said at least one condensed measurement, and as a function of the relation between the error made in the a priori estimation of the motion of the carrier and the error made in said at least one condensed measurement.

US Pat. No. 10,211,946

METHOD AND DEVICE FOR SUPPRESSING INTERFERING SIGNALS IN A SATELLITE PAYLOAD SIGNAL

AIRBUS DEFENCE AND SPACE ...

1. A method for suppressing a spurious signal in a payload signal supplied by a reception antenna of a payload of a satellite, said satellite comprising an array of measurement antennas supplying respective measurement signals, the method comprising steps of:combining each of the measurement signals with the payload signal;
determining reference weighting coefficients of the measurement signals as a function of signals obtained by combining each of the measurement signals with the payload signal for forming a reference beam directed toward a transmitter of the spurious signal;
forming the reference beam by combining the measurement signals weighted based on corresponding reference weighting coefficients;
determining anti-jamming weighting coefficients of the payload signal and of the reference beam as a function of the payload signal and of the reference beam for forming an anti-jammed beam, in which the spurious signal has been suppressed; and
forming the anti-jammed beam by combining the payload signal and the reference beam weighted based on the corresponding anti-jamming weighting coefficients.

US Pat. No. 10,673,527

SATELLITE TELECOMMUNICATIONS SYSTEM COMPRISING AN OPTICAL GATEWAY LINK AND A RADIO GATEWAY LINK, AND CONTROL METHOD

AIRBUS DEFENCE AND SPACE ...

1. A satellite telecommunications system comprising at least one terrestrial user terminal, wherein said system comprises at least one so-called optical gateway satellite in Earth orbit, comprising a payload, said payload comprising:a communication module, referred to as a user module, suitable for exchanging data with said terrestrial user terminal,
a communication module, referred to as a gateway module, suitable for exchanging data in the form of optical signals with at least one terrestrial optical gateway station,
the satellite telecommunications system further comprising:
at least one other so-called radiofrequency-only gateway satellite, comprising a communication module, referred to as a user module, suitable for exchanging data with said user terminal, and a communication module, referred to as a gateway module, suitable for exchanging data solely in the form of radio-frequency signals with at least one radio gateway station,
a control module configured such that said control module determines whether an optical path exists between the optical gateway satellite and an optical gateway station and such that said control module routes the data from the user terminal to the radiofrequency-only gateway satellite in the absence of any optical path.

US Pat. No. 10,554,291

METHOD AND SYSTEM FOR DETECTING USEFUL SIGNALS WITH SIGNIFICANT RESPECTIVE FREQUENCY DRIFTS IN AN OVERALL SIGNAL

AIRBUS DEFENCE AND SPACE ...

1. A method for detecting useful signals in an overall signal, the useful signals being emitted by different terminals in a multiplexing frequency band, each useful signal can be affected by a frequency drift, the overall signal corresponding to radio-frequency signals received in the multiplexing frequency band, wherein the method comprises:a detection phase comprising:
for a plurality of positions of a detection time window relative to the overall signal: calculating a detection frequency spectrum of the overall signal for each detection time window being considered;
detecting the useful signals in the overall signal as a function of the detection frequency spectra; and
an estimation phase comprising, for each useful signal detected:
for a plurality of frequency drift values: readjusting a frequency of the overall signal as a function of the frequency drift value being considered;
calculating an estimation frequency spectrum of the overall signal for each frequency drift value over an estimation time window comprising at least part of the useful signal detected, and of a duration that is longer than that of the detection time window;
estimating the frequency drift affecting the useful signal detected as a function of the estimation frequency spectra.

US Pat. No. 10,527,493

SPECTROPHOTOMETRIC DEVICE WITH A PLURALITY OF SPECTRAL MEASUREMENT BANDS

AIRBUS DEFENCE AND SPACE ...

1. A spectrophotometric device including a plurality of spectral measurement bands, comprising:a telescope having an entrance pupil (PE) and an output focal plane (PF), adapted to focus, in the output focal plane, radiation that enters the telescope through the entrance pupil;
a spectrophotometer having an entrance which is superimposed on the output focal plane (PF) of the telescope, and comprising a spectral spreading component and an array detector which is optically conjugate with the entrance of the spectrophotometer, said detector having a photosensitive surface which extends in a first detection direction (D1) parallel to a direction of spectral spreading produced by the spectral spreading component, and which also extends in a second detection direction (D2) perpendicular to the first detection direction,
a pupil mask arranged in the entrance pupil (PE) of the telescope (10) and having a plurality of apertures (O1-O4) forming separate sub-pupils which are respectively dedicated to the spectral measurement bands;
pupillary separating prisms, which are arranged one-on-one against the apertures (O1-O4) of the pupil mask so that each pupillary separating prism deflects a portion of the radiation which passes through the corresponding sub-pupil in a prismatic deflection direction (X) which is common to all the pupillary separating prisms, and with a prismatic deflection amplitude which is different from that of every other pupillary separating prism, and the spectrophotometer being oriented relative to the pupillary separating prisms so that the second detection direction (D2) optically corresponds to the prismatic deflection direction through the telescope and the spectrophotometer;
a plurality of curved slits which are distributed in the entrance of the spectrophotometer so that the longitudinal direction of the slits optically corresponds to the prismatic deflection direction (X) through the telescope, and the slits being offset from one another so that each receives through one of the apertures (O1-O4) of the pupil mask and one of the pupillary separating prisms, and through the telescope, a respective portion of the radiation which originates from a pointing direction (DP) of the telescope; and
a first set of filters, each determining one of the spectral measurement bands, the filters of the first set being arranged in front of the photosensitive surface of the detector, each filter of said first set being effective within a detection aperture which is superimposed along the second detection direction (D2) on an image of only one of the slits, formed by the spectrophotometer with a portion of the radiation entering the telescope through a single one of the apertures (O1-O4) of the pupil mask, and the detection aperture of each filter extending in the first detection direction (D1).

US Pat. No. 10,450,093

DEVICE FOR ELECTRICAL CONNECTION, METHOD OF ASSEMBLING A FEMALE PART OF THIS CONNECTION DEVICE, SUPERINSULATING BLANKET AND SPACECRAFT

AIRBUS DEFENCE AND SPACE ...

1. A device for electrical connection intended to connect a super-insulating mattress to a structural panel of a spacecraft, said connection device comprising:a sleeve having an axis extending in a first direction, said sleeve comprising a support extending in the first direction,
a conductive pin suitable for being arranged in said sleeve,
an elastic element carried by said support, said elastic element being suitable for exerting a force on the pin in a direction substantially perpendicular to the first direction characterized in that the support is conductive and the sleeve comprises a conductive fastening device suitable for axially fastening the super-insulating mattress, said fastening device comprising:
a flange peripheral to the sleeve and extending in a plan perpendicular to the first direction,
a washer, the super-insulating mattress being intended to be interposed between the washer and the flange, and
a stop established on the free end of the sleeve,and in that said elastic element, made of metal, presses the pin against the sleeve.

US Pat. No. 10,407,186

METHOD AND DEVICE FOR CONTROLLING ATTITUDE OF A SPACECRAFT

AIRBUS DEFENCE AND SPACE ...

1. An attitude control method for a spacecraft rotating on itself with a non-zero total angular momentum Htot, the spacecraft comprising a set of inertia flywheels configured to form an internal angular momentum Hact of any axis in a craft reference frame, the method comprising steps of:aligning an axis of the total angular momentum Htot with a principal axis of inertia of the spacecraft;
controlling the inertia flywheels, during the aligning step, so as to form an internal angular momentum Hact such that a following expression:
Hact×J?1(Htot?J?1Htot)
is negative throughout the duration of the aligning step if a targeted principal axis of inertia is an axis of maximum inertia of the spacecraft, and is positive throughout the duration of the aligning step if the targeted principal axis of inertia is an axis of minimum inertia of the spacecraft;
wherein J in the expression is an inertia matrix of the spacecraft, an operator × is a scalar product between two vectors and an operator is a vector product between two vectors; and
wherein the inertia flywheels are controlled so as to form the internal angular momentum Hact for which an angle ? between the internal angular momentum Hact and the vector J?1(Htot?J?1Htot) bears out, throughout the duration of the aligning step, a following expression: |cos ?|>0.9.

US Pat. No. 10,532,831

METHOD AND SYSTEM FOR ACQUIRING IMAGES VIA A CONSTELLATION OF OBSERVATION SATELLITES

Airbus Defence and Space ...

1. A method for acquiring images using a constellation of satellites in non-geosynchronous Earth orbit, each satellite comprising an inter-satellite communicator and an observation instrument controlled according to a work plan, the work plan comprising a list of acquisitions to be performed, each satellite being configured to exchange data with any of other satellites of the constellation, directly or via one or more other satellites of the constellation, the method comprising steps of:forming an aggregate of work plans intended for different satellites of the constellation;
transmitting, by a ground station, the aggregate of work plans to a satellite of the constellation;
transmitting the aggregate of work plans, by a satellite that received the aggregate of work plans from the ground station, to at least one other satellite of the constellation;
retransmitting the aggregate of work plans by each satellite that received the aggregate of work plan from another satellite to said at least one other satellite of the constellation in response to a determination that the aggregate of work plans comprises a work plan which has not yet been communicated to an intended satellite, said each satellite retrieving an intended work plan for said each satellite from the received aggregate of work plans; and
performing image acquisitions by said each satellite according to the intended work plan for said each satellite extracted from the received aggregate of work plans.

US Pat. No. 10,118,717

ARTIFICIAL SATELLITE

AIRBUS DEFENCE AND SPACE ...

1. An artificial satellite comprising:at least one battery pack configured to dissipate heat,
at least one radiator configured to convey the heat dissipated by the battery pack into space, and
at least one low-dissipation equipment item having an individual power flux density of less than 250 watts/m2,
wherein the artificial satellite comprises a thermally insulating cover delimiting, together with said radiator, an interior isothermal zone in which thermal control takes place by radiation, and
wherein said battery pack and said low-dissipation equipment are arranged in said thermally insulating cover, and said battery pack has an operating range of between 0° C. and 50° C.

US Pat. No. 10,491,561

EQUIPMENT FOR OFFERING DOMAIN-NAME RESOLUTION SERVICES

AIRBUS DEFENCE AND SPACE ...

1. An equipment suitable for offering domain name resolution services, said equipment being intended to be connected to a communication network implementing security domains, said equipment being intended to be declared as a domain name server with client devices in said communication network,said equipment including:
a client interface unit suitable for receiving domain name resolution requests coming from said client devices and for responding to said requests, each domain name resolution request including an IP address of the client device that sent said request and a domain name to be resolved;
an authentication unit suitable for performing first authentication operations checking, for each domain name resolution request, at least by means of the IP address of the client device that sent said request, whether said client device or a user of said client device has previously been registered with said equipment or an external authentication server to which said equipment is connected;
an authorisation unit suitable for performing first authorisation operations checking, for each request for resolution of a domain name authenticated by the authentication unit, whether the client device that sent said request or the user of said client device actually has a right of access to the resources of said domain name; and
a domain name resolution unit suitable for performing domain name resolution operations by means of a cache in which said equipment stores associations of IP addresses and respective domain names,
said cache being populated by means of results of domain name resolutions made by external name servers each corresponding to one of said security domains to which said equipment is intended to be connected via respective secure tunnels and to which said equipment resort to, independently of said security domains, when said cache does not include data allowing to effect the required domain name resolution.

US Pat. No. 10,207,824

RADIATOR DEPLOYABLE FOR A SATELLITE STABILIZED ON THREE AXES

AIRBUS DEFENCE AND SPACE ...

1. A deployable photovoltaic generator for a three-axis stabilized satellite, the photovoltaic generator comprises an array of panels that are hinged to each other, and a supporting yoke to attach the photovoltaic generator to a structure of a body of the satellite, the panels are folded on top of one another in a first or launch position of the photovoltaic generator, the panels are completely deployed in a second or deployed position of the photovoltaic generator; wherein at least some of the panels are solar panels having a photovoltaic-collector side orientable towards solar radiation; wherein at least one panel consists of a thermal radiator to provide a radiator panel; wherein a radiative side of the thermal radiator is oriented oppositely to a side of the photovoltaic panels bearing photovoltaic collectors in the deployed position of the photovoltaic generator, the radiative side is referred to as a shady side, and an opposite side of the panel forming the thermal radiator is referred to as a sunny side; wherein the panel closest the supporting yoke is a panel forming the thermal radiator; and wherein each panel is mono-functional such that thermal-radiator and solar-generator functions are exclusive from each other in each panel of the photovoltaic generator.

US Pat. No. 10,677,533

HEAT EXCHANGE DEVICE FOR ARTIFICIAL SATELLITE, WALL AND ASSEMBLY OF WALLS COMPRISING SUCH A HEAT EXCHANGE DEVICE

AIRBUS DEFENCE AND SPACE ...

1. A wall configured to be mounted in an artificial satellite, the wall comprising:a support panel; and
at least one heat exchange device supported by the support panel, the at least one heat exchange device comprising:
first capillary heat pipes containing a first heat transfer fluid, the first capillary heat pipes forming a first network,
second capillary heat pipes containing a second heat transfer fluid, the second capillary heat pipes forming a second network, and
a solid block provided with a first channel and a second channel independent of the first channel, each of the first channel and the second channel having a capillary internal structure, the capillary internal structure being formed directly on the first channel and the second channel of the solid block,
the first channel having
at least one first opening connected to one of the first capillary heat pipes of the first network, and
at least one first side channel having a longitudinal length extending perpendicularly in a direction through the solid block toward the second channel, and
the second channel having
at least one second opening connected to one of the second capillary heat pipes of the second network, and
at least one second side channel having a longitudinal length extending perpendicularly in a direction through the solid block toward the first channel,
the at least one first side channel of the first channel lying near the at least one second side channel of the second channel such that the first heat transfer fluid is able to exchange heat with the second heat transfer fluid via said at least one first side channel and the at least one second side channel,
wherein the solid block is void of space, except for the first and second channels.

US Pat. No. 10,513,352

METHOD AND SYSTEM FOR TRANSFERRING A SATELLITE FROM AN INITIAL ORBIT INTO A MISSION ORBIT

AIRBUS DEFENCE AND SPACE ...

1. A method of transferring a satellite from an initial orbit to a mission orbit of the satellite around a celestial body, comprising the steps of:in the initial orbit, docking a spacecraft to an external propellant supply unit, the spacecraft comprising an electrical propulsion module and a fluidic propellant supply circuit to supply a propellant to the electrical propulsion module, the external propellant supply unit comprising a propellant tank containing a reserve of the propellant and the external propellant supply unit is being anchored to the satellite by anchors which cooperate and which are carried respectively by the external propellant supply unit and the satellite;
wherein the spacecraft and the external propellant supply unit comprise docking units which cooperate to reversibly dock with each other, the docking units comprising fluidic connectors to provide a fluidic connection between the propellant tank and the fluidic propellant supply circuit to supply the propellant to the electrical propulsion module from the external propellant supply unit during the docking step;
moving the spacecraft docked to an assemblage comprising the external propellant supply unit anchored to the satellite, to the mission orbit of the satellite by the electrical propulsion module of the spacecraft supplied with the propellant from the propellant tank of the external propellant supply unit;
releasing the satellite into the mission orbit; and
wherein during the moving step, the electrical propulsion module of the spacecraft is supplied with the propellant directly from the propellant tank of the external propellant supply unit, without going through any reservoir belonging to the spacecraft.

US Pat. No. 10,400,804

DEVICE FOR THE SHOCK-ABSORBING ATTACHMENT OF TWO ELEMENTS TO BE ASSEMBLED, METHOD FOR PRODUCING SUCH A DEVICE, SET OF TWO ELEMENTS ASSEMBLED USING SUCH A DEVICE, AND ASSEMBLY METHOD

AIRBUS DEFENCE AND SPACE ...

1. Device (1) for the shock-absorbing attachment of two elements (2, 3) to be assembled, the attachment device comprising:an inner part (4) that is tubular along an axis of attachment (A) intended to be rigidly attached to an element (3) to be assembled, and comprising an outer lateral surface (5);
an outer part (11) that is tubular along the axis of attachment (A), and is hollow, intended to be rigidly attached to another element (2) to be assembled and comprising an inner lateral surface (12), the inner part (4) being accommodated in the outer part (3) so that the outer surface of the inner part is facing the inner surface of the outer part;
an elastomer layer (18) between the outer part (11) and the inner part (4),wherein the outer lateral surface (5) of the inner part (4) comprises at least one irregular portion and the inner lateral surface (12) of the outer part (11) comprises at least one irregular portion complementary to the irregular portion of the outer surface (5) of the inner part (4), the elastomer layer (18) comprising a first face (19) bonded to the irregular portion of the lateral outer surface (5) of the inner part (4), and a second face (20) opposite to the first face (19), bonded to the irregular portion of the lateral inner surface (12) of the outer part (11), wherein the irregular portion of the inner part (4) and the irregular portion of the outer part (5) overlap one another radially of the axis of attachment (A) and wherein the elastomer layer (18), when viewed in cross-section in a longitudinal plane (P) comprising the axis of attachment (A), comprises:at least two portions (27a, 27b, 37a, 37b, 29a, 29b), called transverse, working in a direction that is transverse to the axis of attachment (A), a first portion (27a, 29a, 37a) being situated on a first side of the axis of attachment (A) and the second portion (27b, 29b, 37b) being situated on the other side of the axis of attachment (A), and
wherein the elastomer layer, when viewed in cross-section in a longitudinal plane comprising the axis of attachment, comprises on each side of the axis of attachment, at least three portions, called longitudinal, distributed in the direction of the axis of attachment with a predetermined pitch, at least one of the three longitudinal portions working against the other two portions in the direction of the axis of attachment.

US Pat. No. 10,442,557

SATELLITE COMPRISING AN OPTICAL PHOTOGRAPHY INSTRUMENT

AIRBUS DEFENCE AND SPACE ...

1. A satellite comprising:at least one image capturing optical instrument comprising a main objective having an optical axis, the optical instrument having a field of view;
at least one launch vehicle interface system configured to be removably secured to a satellite interface system of a satellite launch vehicle; and
a linking device between the launch vehicle interface and the optical instrument, extending substantially parallel to the optical axis of the main objective between an upper end and a lower end;
wherein the launch vehicle interface system is connected to the linking device by the lower end, and
wherein the optical axis of the optical instrument is directed from the upper end towards the lower end of the linking device, the launch vehicle interface system being outside the field of view of the instrument.

US Pat. No. 10,207,825

TELECOMMUNICATIONS SATELLITE ARCHITECTURE

AIRBUS DEFENCE AND SPACE ...

1. A telecommunications satellite stabilized on three axes, comprising:a set of dissipative equipment constituting a satellite payload, the satellite is substantially parallelepipedal in form with east and west panels forming two opposing faces, the satellite comprises supporting data transmission antennas, and north and south panels forming two other opposing faces, the north and south panels comprising, on their outer faces, radiator surfaces configured to cool an electronic equipment of the satellite; and
wherein the dissipative equipment installed on the north and south panels is configured to dissipate a thermal power corresponding to less than 25% of a total dissipated power of the electronic equipment of the payload.

US Pat. No. 10,200,830

METHOD FOR MANAGING FLOOR CONTROL ON A COMMUNICATION CHANNEL IN THE CONTEXT OF HALF-DUPLEX COMMUNICATIONS

AIRBUS DEFENCE AND SPACE ...

1. A method for managing floor control on a shared communication channel in the context of half-duplex communications implemented in a communication network composed of a plurality of interconnected sub-networks, each sub-network being associated with a supernode device of the communication network, the method being implemented by one said supernode device, wherein, when a first floor request is received from a terminal device of the sub-network with which said supernode device is associated and said supernode device is not aware of at least one second floor request with higher priority, the method comprising:propagating, by said supernode device, the first floor request to each other supernode device;
transmitting, by said supernode device, a floor pre-grant message to said terminal device so as to enable said terminal device to take the floor;
transmitting, by said supernode device, a floor pre-grant notification message to each other terminal device in the sub-network with which said supernode device is associated, so that each said other terminal device listens to the shared communication channel;
determining, by said supernode device, a timer duration according to a distribution law f?(t) for time period between floor release and a next floor control, and a distribution law f?(d) for network latency between an instant at which a floor request is transmitted by a terminal device and an instant at which said request is actually received by said supernode device, so that the probability Pfail of dismissing said terminal device of the floor control is below a first predefined threshold;
storing, by said supernode device, in a buffer data received from said terminal device in the context of floor control, and propagating said data to each other supernode device;
activating, by said supernode device, the buffer in read mode for broadcasting the stored data to each terminal device being listening on the sub-network associated with said supernode device, when said timer has elapsed; and
wherein, when the first floor request is received from a terminal device in a sub-network other than the one with which said supernode device is associated and said supernode device is not aware of at least one second floor request with higher priority, the method further comprising:
transmitting, by said supernode device, a floor pre-grant notification message to each terminal device in the sub-network with which the supernode device is associated, so that each terminal device in said sub-network listens to the shared communication channel;
determining, by said supernode device, the duration of the timer according to the distribution law f?(t) and the distribution law f?(d), so that the probability Pfail of dismissing said terminal device of the floor control is below the first predefined threshold;
storing, by said supernode device, in the buffer data propagated by another supernode device in the context of floor control;
activating, by said supernode device, the buffer in read mode for broadcasting the stored data to each terminal device being listening on the sub-network associated with said supernode device, when said timer has elapsed; and
wherein, when said supernode device detects at least one second floor request with higher priority before expiry of said timer, said supernode device releases the buffer and, when said first request has been received from a terminal device in the sub-network with which said supernode device is associated, said supernode device notifies said terminal device that said terminal device is refused floor control.

US Pat. No. 10,689,133

SATELLITE WITH CYLINDRICAL MAIN BODY, STACK COMPRISING SUCH A SATELLITE AND LAUNCH ASSEMBLY FOR SUCH A SATELLITE

AIRBUS DEFENCE AND SPACE ...

1. A satellite comprising:a main body having a cylindrical shape, the main body having an inner wall delimiting an inner space and an outer wall extending along a main axis between a lower end surface and an upper end surface, the lower end surface comprising an interface mechanism configured to engage with a complementary interface mechanism of a launcher;
at least one internal item of equipment, fixed onto the inner wall of the main body and extending at least partially into the inner space in which the outer wall of the main body comprises at least a portion of plane surface, forming a facet, the internal item of equipment comprising an optical imaging instrument, and electronics associated with the optical instrument, the optical instrument comprising a sighting axis oriented parallel to the main axis of the main body; and
at least one external item of equipment fixed onto the outer wall of the main body, the external item of equipment extending as a transverse projection from the outer wall with respect to the main axis, the at least one external item of equipment being either a tank of propellants or an inertial actuator, the external item of equipment being fixed on the at least portion of plane surface that forms the facet.

US Pat. No. 10,684,329

METHOD FOR ESTIMATING THE AGEING OF A BATTERY

AIRBUS DEFENCE AND SPACE ...

1. A method for estimating the ageing of a Li-Ion type battery powering an electrical system, comprising:a reference ageing test to determine a model of evolution of the impedance of the Li-Ion type battery with ageing, the model based on measurements in a frequency interval 0.01-3 Hz and subsequently conducting:
testing the Li-Ion type battery during a normal operation of the Li-Ion type battery throughout a life of the Li-Ion type battery;
acquiring a set of data about the voltage and current across the battery terminals, in response to current perturbations provoked during the normal operation of the Li-Ion type battery by changes of consumption rate of the electrical system;
determining an impedance of the Li-Ion type battery throughout the life of the Li-Ion type battery during the normal operation of the Li-Ion type battery, within a predetermined frequency interval, from the voltage and current data by:
identifying parameters of a predetermined model structure from measured voltage and current data, the model structure configured to model a time-discrete battery as a linear combination of past input, output and perturbation data;
converting the identified model into a frequency domain;
computing a low-frequency impedance of the Li-Ion type battery; and
determining an ageing profile of the Li-Ion type battery based on the impedance of the Li-Ion type battery determined from the voltage and current data obtained throughout the life of the Li-Ion type battery during the normal operation of the Li-Ion type battery to estimate an age of the Li-Ion type battery as a function of the impedance by comparing the impedance with a previously stored model of evolution of the impedance with ageing, the predetermined frequency interval being in 0.01-3 Hz band, and to determine an end of life of the electrical system.

US Pat. No. 10,931,364

SATELLITE PAYLOAD COMPRISING A DUAL REFLECTIVE SURFACE REFLECTOR

Airbus Defence and Space ...

1. A payload of a satellite of a satellite telecommunication system, said payload comprising:a reflector,
a network of sources, and
a beam-forming network connected to said sources,
wherein said network of sources is configured to process beams which transport signals both in a first frequency band (band B1) and in a second frequency band (band B2), each of the beams processed by a plurality of the sources in said network of sources, and each of the plurality of sources of the network of sources is configured to process the beams for band B1 and for band B2,
wherein the reflector comprises two reflective surfaces positioned one behind the other and aligned such that a straight line projects through the two reflective surfaces and through the network of sources,
wherein the two reflective surfaces have different curvatures so that each reflective surface of the two reflective surfaces produces an image of the network of sources with a different magnification factor,
wherein a first of the reflective surfaces is closer to the network of sources and is transparent for all signals transported on the band B2 and configured to reflect signals transported in the band B1, and
wherein a second of the reflective surfaces is configured to reflect signals transported in the band B2.

US Pat. No. 10,921,355

METHOD AND SYSTEM FOR DETECTING USEFUL SIGNALS, WITH RESPECTIVE NON-NEGLIGIBLE FREQUENCY DRIFT, IN A TOTAL SIGNAL

AIRBUS DEFENCE AND SPACE ...

1. A method for detecting a plurality of useful signals in a total signal, each useful signal being of a finite duration and subjectable to a frequency drift that is greater, over the duration of said each useful signal, than a spectral width of said each useful signal, the plurality of useful signals corresponding to radiofrequency signals transmitted by terminals in a multiplexing frequency band, the total signal corresponding to all of the radiofrequency signals received in the multiplexing frequency band, the method comprising:calculating multiple spectrograms associated with linear frequency drift values, respectively, each spectrogram being representative of values of a frequency spectrum of the total signal at analysis frequencies in the multiplexing frequency band, and of time variations of the values of the frequency spectrum at analysis times within an analysis time window by compensating for a linear frequency drift under consideration;
for each analysis frequency and each spectrogram, time envelope filtering of the values of the frequency spectrum at the analysis times of said each spectrogram at said each analysis frequency, using a filter representative of a reference time envelope of the plurality useful signals; and
detecting a useful signal at an analysis time and at an analysis frequency in response to a verification of a predefined detection criterion by a filtered spectrogram for said analysis time and said analysis frequency, the filtered spectrogram being a value of a spectrogram obtained by the time envelope filtering.

US Pat. No. 10,689,134

DEVICE FOR CONTROLLED SEPARATION BETWEEN TWO PARTS AND USE OF SUCH A DEVICE

AIRBUS DEFENCE AND SPACE ...

1. A separation device for controlled separation of a first stationary part and a second mobile part, the stationary part having a thermal expansion coefficient different from that of the mobile part, the separation device comprising:at least one bonding agent placed in a layer between a stationary connecting surface of the stationary part and an opposite mobile connecting surface of the mobile part,
at least one device for heating at least one of the stationary part and the mobile part, and
at least one control system of the heating device,
wherein the at least one bonding agent has a decomposition temperature greater than a heating temperature of the heating device.

US Pat. No. 11,032,817

METHOD OF TRANSMISSION, BY A TERMINAL OF A SLOT-BASED ACCESS COMMUNICATION SYSTEM, OF A MESSAGE WITH INTRA-MESSAGE FREQUENCY HOPS

AIRBUS DEFENCE AND SPACE ...

1. A method for emission, by a terminal, of a message to a receiver station of a wireless communication system, the terminal being time synchronized with the receiver station, the message emitted over a channel shared with other terminals and on which the emission of messages to the receiver station is carried out at beginning of predetermined time intervals for the terminal and the receiver station, called predetermined slots, and the method comprising:encoding data to be included in the message to be emitted by a channel encoder;
distributing the encoded data among Nb sub-messages of the message to be emitted, by fragmenting the encoded data into Nb fragments, Nb being an integer greater than or equal to two;
randomly selecting a slot, among the predetermined slots, for the emission of the message by the terminal;
selecting Nb emission frequencies, respectively associated with the Nb sub-messages, by the terminal, wherein the Nb emission frequencies are not known a priori to the receiver station; and
emitting the message at the beginning of the selected slot, by successively emitting the sub-messages on their respective associated emission frequencies.

US Pat. No. 10,912,009

METHOD FOR DISCOVERING A NODE OF AN AD HOC NETWORK

AIRBUS DEFENCE AND SPACE ...

1. A method for discovering a node of an ad hoc network among a plurality of mobile nodes, the method comprising:periodically transmitting, by an antenna of a first mobile node, a first radiofrequency signal including an invitation token, the invitation token comprising data relating to an identity of the node which transmits said invitation token;
detecting, by a second mobile node, the first signal and extracting the data contained in the invitation token of the first node;
transmitting, by an antenna of the second node, a second radiofrequency signal including at least one acknowledgement of the invitation token, said transmission being carried out in an assigned time window subsequent to the reception by the second node of the invitation token;
creating a radio bubble subsequent to the reception by the first node of at least acknowledgement of the invitation token, communications between the nodes of the radio bubble being coordinated by the transmission of a speech token between said nodes, the transmission of said speech token between the nodes of a radio bubble defining a transmission sequence between the different nodes;
creating an IP sub-network between the nodes of the radio bubble, each node including an IP address within the IP sub-network range;
wherein the speech token or the invitation token includes:
a priority indicator of a node of the radio bubble indicating the maximum number of nodes with which said radio interface can form a radio bubble and;
an indicator of a transmission mode among a looped mode and a relayed mode specifying, if needed, the identity of the relay node.

US Pat. No. 10,887,004

TELECOMMUNICATIONS SATELLITE, BEAMFORMING METHOD AND METHOD FOR MANUFACTURING A SATELLITE PAYLOAD

AIRBUS DEFENCE AND SPACE ...

1. A telecommunications satellite intended to be placed in earth orbit, comprising an antenna having a reflector and an array of feed elements wherein:said satellite comprises adaptive analogue beam-forming networks, said adaptive analogue beam-forming networks being connected to different respective groups of feed elements of the array of feed elements, said groups of feed elements serving different respective geographic regions on the Earth's surface,
each adaptive analogue beam-forming network is suitable for simultaneously activating a predetermined number of beams serving respective geographic zones within the geographic region served by the group of feed elements to which said beam-forming network is connected,
said satellite comprises a module for controlling said adaptive analogue beam-forming networks, configured so as to modify the active beams of each adaptive analogue beam-forming network,
each group of feed elements comprises feed elements shared with other groups of feed elements, and
at least one geographic region has a geographic overlap of at least 30% with other geographic regions.

US Pat. No. 10,773,832

PROJECTILE INTENDED FOR DAMPING A SPACECRAFT AND CORRESPONDING SPACE DELIVERY VEHICLE

AIRBUS DEFENCE AND SPACE ...

1. A projectile configured to damp a spacecraft including a main body and an active attitude control system configured to provide 3-axis stabilization of the attitude of said spacecraft, said projectile comprising:a harpoon; and
a passive damper fixedly mounted on said harpoon and configured to generate, in cooperation with the magnetic field of the Earth, a damping torque to damp the spacecraft when the passive damper is fixed to the spacecraft, said passive damper comprising an outer enclosure comprising an inner surface, and
an inner body positioned inside said outer enclosure and configured to move in rotation inside said outer enclosure about at least one axis of rotation, the inner body being permanently magnetized, said inner body comprising an outer surface, said inner surface of the outer enclosure and the outer surface of the inner body being separated by a viscous fluid,
wherein said outer enclosure is configured to be fixed to the main body of said spacecraft for rotation therewith in a state in which the harpoon is secured to said main body,
the projectile is configured to be connected to a space delivery vehicle, that is different from the spacecraft, in order to be projected from said space delivery vehicle towards said spacecraft, and
the inner surface of the outer enclosure and the outer surface of the inner body respectively have a cylindrical shape.

US Pat. No. 10,619,627

METHOD FOR CONTROLLING THE TEMPERATURE OF AN ELECTRIC PROPULSION SYSTEM

AIRBUS DEFENCE AND SPACE ...

1. A method for controlling a temperature of an electric propulsion system, the electric propulsion system comprising a discharge channel, an anode, a cathode, an injection system to inject a propellant gas in the discharge channel, and a magnetic circuit comprising at least one magnetic winding to generate a magnetic field in the discharge channel, the method comprising steps of: determining the temperature at a reference thermal point of the electric propulsion system; and heating the electric propulsion system by a Joule effect, through an application of a first current in the magnetic circuit in response to a determination that the temperature at the reference thermal point is below a predetermined minimum temperature during a stop phase of the electric propulsion system.

US Pat. No. 11,037,011

METHOD FOR OBSERVING THE SURFACE OF THE EARTH AND DEVICE FOR IMPLEMENTING SAME

Airbus Defence and Space ...

1. A method for acquiring images of the surface of the Earth, comprising:placing of a first aerial or space platform in a stationary position above said surface of the Earth or moving at a speed less than 200 km/h above said surface of the Earth, said first platform comprising a first image acquisition system with a field of view covering a zone, called zone of interest, of said surface of the Earth,
placing of a second aerial or space platform in a stationary position above said surface of the Earth or moving at a speed less than 200 km/h above said surface of the Earth, said second platform comprising a second image acquisition system with a narrower field of view and of better resolution than the first image acquisition system, the field of view of said second image acquisition system being orientable such that a field of regard of said second image acquisition system covers said zone of interest,
implementing an observation cycle comprising steps of:
(a) acquiring an image of said zone of interest by said first image acquisition system,
(b) partitioning of the image thus acquired, called preliminary image, in mesh units each corresponding to a sector of said zone of interest capable of being included in the field of view of the second image acquisition system,
(c) analysing said preliminary image, to detect potential presence of marks representative of unwanted elements in or above the zone of interest,
(d) identifying mesh units of said preliminary image comprising no mark representative of unwanted elements, said mesh units comprising no mark representative of unwanted elements corresponding to so-called favourable sectors of said zone of interest,
(e) and, if applicable, acquiring an image, called final image, of favourable sector(s) by said second image acquisition system,
and, if a predetermined rate of sectors of the zone of interest for which a final image has been acquired by the second image acquisition system has not been achieved, repeat(s) of the observation cycle until said rate is achieved.