US Pat. No. 9,183,983

MODULAR EQUIPMENT CENTER INTEGRATED TRUSS SENSORS

THE BOEING COMPANY, Chic...

1. A system for powering a line replaceable unit (LRU) without exposed electrical connectors, the system comprising:
a truss assembly comprising a plurality of transfer layers;
a primary coil of an inductive power coupling system within one or more of the transfer layers of the truss assembly; and
a secondary coil of the inductive power coupling system within the LRU, wherein the primary coil induces a current in the
secondary coil when the secondary coil within the LRU is in proximity of the primary coil within the truss assembly.

US Pat. No. 9,090,357

METHOD OF ASSEMBLING PANELIZED AIRCRAFT FUSELAGES

The Boeing Company, Chic...

1. A method of assembling a panelized aircraft fuselage, the method comprising:
loading a keel structure on a cradle;
attaching stanchions to a floor grid;
positioning the floor grid and stanchions over the keel structure and attaching the stanchions to the keel structure;
obtaining a full fuselage contour including locating lower panels on the floor grid while using the cradle, the floor grid,
and the keel structure to support the lower panels, and locating upper panels on the lower panels; and

fastening the lower panels to the keel structure and the upper panels,
wherein the fuselage is assembled upright from the keel structure without changing orientation of the fuselage.

US Pat. No. 9,482,180

THRUST REVERSER SYSTEM

The Boeing Company, Chic...

1. An apparatus comprising:
a sleeve configured to move between a first position and a second position, wherein the sleeve exposes a cascade when in the
second position;

at least one linear electric motor directly connected to the sleeve and configured to move the sleeve between the first position
and the second position, wherein the at least one linear electric motor comprises: a coil system disposed within a base connected
to an engine structure, a member connected to the sleeve, and a magnet system connected to the member and configured to interact
with the coil system to linearly move the member relative to the base to cause the sleeve to move between the first position
and the second position;

a controller configured to control operation of the at least one linear electric motor to move the sleeve between the first
position and the second position; and

a load cell, disposed within the base, configured to send load information to the controller, wherein the controller is further
configured to use the load information to maintain a desired load on the at least one linear electric motor.

US Pat. No. 9,475,585

TILT-ROTOR VERTICAL-LIFT AIRCRAFT

The Boeing Company, Chic...

1. An aircraft, comprising:
a fuselage comprising a higher portion and a lower portion;
two fixed wings coupled to and extending from opposing sides of the lower portion of the fuselage;
a tilt-rotor assembly coupled to each of the two fixed wings;
at least two engines, non-movably coupled to each of the two fixed wings at locations on the two fixed wings between the fuselage
and a respective one of the tilt-rotor assemblies;

a common power transmission system, operatively coupling the tilt-rotor assemblies to the at least two engines coupled to
each of the two fixed wings, wherein the common power transmission system comprises:

a mid-wing gearbox positioned within the fuselage between the two fixed wings;
a first driveshaft that extends between the mid-wing gearbox and a first of the tilt-rotor assemblies and a second driveshaft
that extends between the mid-wing gearbox and a second of the tilt-rotor assemblies, wherein the mid-wing gearbox evenly distributes
mechanical rotational energy between the first and second driveshafts at least while all of the at least two engines, non-movably
coupled to each of the two fixed wings, are operable; and

at least four driveshaft gearboxes coupled to the two fixed wings, wherein each of the at least four driveshaft gearboxes
is in power receiving communication with a respective one of the at least two engines, coupled to each of the two fixed wings,
and each of the at least four driveshaft gearboxes evenly distributes mechanical rotational energy from the respective one
of the at least two engines, coupled to each of the two fixed wings, to respective sections of one of the first and second
driveshafts coupled with each of the at least four driveshaft gearboxes;

wherein: each tilt-rotor assembly comprises blades, rotatable about a common plane of rotation, and rotation of the first
and second driveshafts rotates the blades of the first and second of the tilt-rotor assemblies, respectively;

each tilt-rotor assembly is rotatable, relative to the two fixed wings, between a vertical orientation, in which the common
plane of rotation is a horizontal plane, and a horizontal orientation, in which the common plane of rotation is a vertical
plane, perpendicular to the horizontal plane; and

the blades of each tilt-rotor assembly rotate about the horizontal plane, to generate the entire lift and no forward thrust
of the aircraft, and about the vertical plane, to generate the entire forward thrust and no lift of the aircraft.

US Pat. No. 9,048,548

AIRCRAFT MISSILE LAUNCHER COVER

The Boeing Company, Chic...

1. A cover for a rail missile launcher having a launch rail comprising: a flightworthy cover adapted for reducing a radar
cross section of the missile launcher and a hanger for slidably mounting the cover on the launch rail.

US Pat. No. 9,470,967

MOTION-BASED SYSTEM USING A CONSTANT VERTICAL RESOLUTION TOROIDAL DISPLAY

The Boeing Company, Chic...

1. A vehicle simulation system, comprising:
a vehicle simulator control system;
a motion platform capable of responding to motion signals from the vehicle simulator control system;
a simulated vehicle control center mounted to the motion platform; and
a visual display system mounted to the motion platform and substantially surrounding the simulated vehicle control center,
the visual display system including

a plurality of image projectors capable of projecting a simulated visual display around the simulated vehicle control center,
and

an image projection screen capable of receiving the simulated visual display from the plurality of image projectors on a convex
portion of the image projection screen, the image projection screen being a toroidal constant vertical resolution surface
defined by a constant vertical resolution elevation curve being at least partially rotated about at least a portion of a central
vertical axis intersecting with a design eye-point of a viewer relative to the simulated vehicle control center to produce
the toroidal constant vertical resolution surface in a vertical direction as a function of elevation.

US Pat. No. 9,284,727

ACOUSTIC BARRIER SUPPORT STRUCTURE

The Boeing Company, Chic...

1. A structure for blocking acoustic wave energy, the structure comprising:
a support structure; and
at least one resonant membrane covering a cell of the support structure wherein the at least one resonant membrane has an
anti-resonant frequency;

wherein the support structure has principal odd resonant frequencies that exceed the anti-resonant frequency of the at least
one resonant membrane.

US Pat. No. 9,274,086

MAGNETIC SHIELDING OF SERVO-MOTORS IN MAGNETIC DETECTION SYSTEMS

THE BOEING COMPANY, Chic...

1. A magnetic detection system, comprising:
an unmanned platform;
a magnetic anomaly detection sensor located onboard the unmanned platform;
a servo-motor including collective external surfaces and located onboard the unmanned platform; and
a magnetic shield disposed onboard the unmanned platform to enclose or to substantially enclose the servo-motor and to reduce
magnetic noise that the magnetic anomaly detection sensor receives from the servo-motor,

wherein the magnetic shield comprises first and second magnetic shield portions detachably mated together, wherein the collective
external surfaces are disposed substantially within a first cavity formed by the first magnetic shield portion, and the collective
external surfaces are disposed substantially within a second cavity formed by the second magnetic shield portion.

US Pat. No. 9,398,676

SYSTEM AND METHOD FOR QUANTIFYING X-RAY BACKSCATTER SYSTEM PERFORMANCE

THE BOEING COMPANY, Chic...

1. A system for quantifying x-ray backscatter system performance, the system comprising:
a support;
a plurality of rods mounted on the support;
the rods of the plurality of rods arranged parallel to each other, having generally curved outer surfaces, and being arranged
in groups of varying widths, each group of the groups having at least two of the rods of a same width; and

a user interface connected to receive a backscatter signal from an x-ray backscatter detector associated with an x-ray tube,
and generate a display representing photon counts of x-ray backscatter for each rod of the plurality of rods from x-rays transmitted
by the x-ray tube.

US Pat. No. 9,301,401

NANOTUBE ELECTRONICS TEMPLATED SELF-ASSEMBLY

THE BOEING COMPANY, Chic...

1. A system for assembling carbon nanotube electronics, the system comprising:
a substrate, wherein the substrate has at least one plurality of posts, the at least one plurality of posts being fabricated
at a predetermined distance from one another;

a fluid matrix containing functionalized carbon nanotubes, wherein the functionalized carbon nanotubes comprise a first end,
a middle, and a second end, wherein the first end and the second end have a relative concentration of functional groups different
from that of the middle such that the functionalized carbon nanotubes exhibit relative electrical charges at the first end
and the second end;

an agitation source, wherein providing agitation of the fluid matrix to preferentially adhere the first end of a functionalized
carbon nanotube to a first one of the at least one plurality of posts and adheres the second end of the functionalized carbon
nanotube to a second one of the at least one plurality of posts due to the relative electrical charges at the first end and
the second end, wherein a connection is formed between the first one and the second one of the at least one plurality of posts.

US Pat. No. 9,242,393

APPARATUS FOR FABRICATING HIGHLY CONTOURED COMPOSITE STIFFENERS WITH REDUCED WRINKLING

THE BOEING COMPANY, Chic...

1. Apparatus for forming a substantially wrinkle-free fiber reinforced composite stiffener having an out-of-plane curved section
along its length, comprising:
a mandrel on which fiber reinforced composite plies may be formed, the mandrel having a sidewall comprising a first tool face,
the sidewall including a first portion along a first length that is less than a total length of the sidewall, the sidewall
further including a second portion along a second length that is less than the total length and a third portion along a third
length that is less than the total length, the first portion being between the second portion and the third portion, the first
portion having an out-of-plane curvature and an in-plane curvature, the second portion having a second curvature different
than the in-plane curvature and the out-of-plane curvature, the third portion having the second curvature, the mandrel further
having a second tool face along the sidewall and connected to the sidewall at an angle, the second tool face also having the
out-of-plane curvature along the first length, and the second tool face further having the second curvature along the second
length and the third length.

US Pat. No. 9,234,740

SHEAROGRAPHIC INSPECTION SYSTEM USING A LASER MATRIX

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a matrix of lasers, wherein the lasers of the matrix are arranged in rows and columns, the matrix including at least four
lasers, the matrix being configured to generate beams of coherent light in an area on a surface of an object, and wherein
a number of speckle patterns in light reflected from the surface of the object form in response to the beams of coherent light
in the area;

a support structure for the matrix;
a camera system configured to generate images of the area, in which the number of speckle patterns are present in the images;
wherein the object is inspected via the apparatus;
wherein the support structure has a first side and a second side;
wherein the support structure has a first flange and a second flange;
wherein a plurality of wheels that are not motorized are connected to the first flange and the second flange;
wherein movement of support structure is provided by a robotic arm;
wherein the matrix of lasers is associated with the second side of the support structure; and
wherein the camera system is positioned to generate images through optics located on the second side of the support structure.

US Pat. No. 9,359,060

LAMINATED COMPOSITE RADIUS FILLER WITH GEOMETRIC SHAPED FILLER ELEMENT AND METHOD OF FORMING THE SAME

The Boeing Company, Chic...

1. A laminated composite radius filler for a composite structure comprising:
a stacked ply assembly comprising a plurality of stacks of laminate radius filler plies cut to a desired width and having
a desired ply orientation; and,

a separate, pre-formed geometric shaped filler element comprising a plurality of plies comprised of a plurality of unidirectional
fibers, a unidirectional fiber tape, a prepreg unidirectional tape, a unidirectional composite tow, a slit unidirectional
tape, a carbon fiber-reinforced plastic (CFRP) tape, a carbon fiber-reinforced plastic (CFRP) fabric, a prepreg fabric, a
woven fabric including a woven carbon fiber fabric, or a combination thereof, the geometric shaped filler element positioned
within the laminated composite radius filler at a desired location on a first portion of the stacked ply assembly, the geometric
shaped filler element deforming a second portion of the stacked ply assembly stacked over the geometric shaped filler element,
such that the laminate radius filler plies of the second portion of the stacked ply assembly change direction and have a component
of direction comprising a horizontal direction and a vertical direction, the laminated composite radius filler having a shape
substantially corresponding to a radius filler region of the composite structure and filling the radius filler region.

US Pat. No. 9,440,737

APPARATUS TO ADJUST AIRFOILS OF ROTOR BLADES

THE BOEING COMPANY, Chic...

1. An apparatus, comprising:
means for adjusting a pitching moment of a rotor blade, the rotor blade including a leading edge, a trailing edge opposite
the leading edge, a first surface, a second surface opposite the first surface, and a tab, the first and second surfaces extending
from the leading edge to the trailing edge, the trailing edge being defined by a convergence of the first and second surfaces,
the tab extending from the trailing edge, the means for adjusting the pitching moment including a forward edge, an aft edge,
a middle portion, a third surface, and a fourth surface, the aft edge opposite the forward edge, the middle portion positioned
between the forward and aft edges, the third surface extending from the forward edge to the middle portion, the third surface
to be attached to the first surface of the rotor blade, the fourth surface extending from the middle portion to the aft edge,
the fourth surface to be attached to the tab, the middle portion to be positioned immediately adjacent an intersection of
the trailing edge and the tab, the tab to extend beyond the aft edge of the means for adjusting the pitching moment, when
the means for adjusting the pitching moment is attached to the rotor blade.

US Pat. No. 9,253,816

SELF-CONTAINED AREA NETWORK SYSTEM

THE BOEING COMPANY, Chic...

1. A portable wireless communications node comprising:
a portable platform;
a battery system connected to the portable platform;
an energy harvester connected to the portable platform and configured to charge the battery system;
a group of antennas;
an antenna platform comprising:
a mounting structure;
a mounting post connecting the mounting structure to the portable platform;
a number of interfaces in the mounting structure; and
a number of mounting units connected to the mounting structure at the number of interfaces and connected to a number of antenna
elements for the group of antennas, wherein a mounting unit in the number of mounting units is configured to receive an antenna
element in the number of antenna elements;

a transceiver connected to the portable platform and the group of antennas, wherein the transceiver receives power from the
battery system and is configured to send and receive radio frequency signals through the group of antennas; and

a wireless communications system that comprises the transceiver and is configured to provide three or more of WiFi access,
cellular communications, tactical radio frequency communications, and satellite communications via the group of antennas.

US Pat. No. 9,063,544

AERIAL FOREST INVENTORY SYSTEM

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
an unmanned aerial vehicle;
an electromagnetic energy sensor system associated with the unmanned aerial vehicle, wherein the electromagnetic energy sensor
system is configured to generate information about a forest; and

a survey controller configured to:
identify a number of locations over the forest in which an information level of the information generated about the forest
by the electromagnetic energy sensor system is reduced by an effect of cloud cover,

generate a route for the unmanned aerial vehicle to move to the number of locations, and
continuously generate the route as changes in cloud cover occur over the forest;
wherein the route is based on a current location of a number of clouds and a prediction of movement of the number of clouds.

US Pat. No. 9,253,823

METAL MATRIX COMPOSITE USED AS A HEATING ELEMENT

The Boeing Company, Chic...

1. A structural substrate for an aircraft structure, comprising:
a multi-layer hybrid composite material comprising:
an outermost layer comprising an electrically conductive metal matrix composite operable to conduct electricity to provide
electric heating;

an intermediate layer comprising an electrical insulator coupled to the outermost layer; and
an innermost layer comprising a second composite coupled to the intermediate layer, the intermediate layer operable to electrically
insulate the outermost layer from the innermost layer.

US Pat. No. 9,057,593

DUAL-FUNCTION GAGE FOR MEASURING DIMENSIONS OF A FASTENER ASSEMBLY

The Boeing Company, Chic...

1. An apparatus comprising:
a gage body;
a shaft which is axially displaceable relative to said gage body;
a digital indicator coupled to said gage body and configured to measure axial displacement of said shaft relative to said
gage body;

a first contact member coupled to said shaft, said first contact member having a first contact surface;
a second contact member coupled to said shaft, said second contact member having a second contact surface offset from said
first contact surface; and

a gage plug insertable into an interior space bounded at least in part by said gage body and having a slot, said gage plug
being rotatable and axially displaceable relative to said gage body and said slot being parallel to said shaft when said gage
plug is inserted into said interior space,

wherein when said gage plug is in a first angular position relative to said gage body, said second contact member is aligned
with said slot, and when said gage plug is in a second angular position different than said first angular position, said second
contact member is not aligned with said slot.

US Pat. No. 9,245,170

POINT CLOUD DATA CLUSTERING AND CLASSIFICATION USING IMPLICIT GEOMETRY REPRESENTATION

THE BOEING COMPANY, Chic...

1. An image processing system comprising:
a data repository, including at least one storage device on a computer system, configured to store image data comprising points
in a point cloud; and

an image processor and program code, which when executed perform operations on the image data, including:
placing the image data into a three-dimensional mesh, comprising:
placing points into a number of cells in the three-dimensional mesh based on three-dimensional locations of the points; and
generating implicit geometry data for the number of cells using the points placed into the number of cells, implicit geometry
data being one of a representation of points relative to each of the number of cells in the three-dimensional mesh and values
based on the relationship of points located within the number of cells, wherein the three-dimensional mesh comprises metadata
including attributes comprising one or more of population, distance, and validity;

identifying vectors of the image data in the three-dimensional mesh, wherein each vector of the vectors comprises a corresponding
vertical array of single cells in the three dimensional mesh;

identifying clustering data using the vectors, wherein the clustering data comprises a plurality of clusters;
assigning a label to each of the plurality of clusters based on a probability that a given cluster represents a given object;
thereafter defining classes by one or more of the plurality of clusters, the classes comprising identifications of the given
object;

extracting feature vectors from the classes and comparing additional vectors to the feature vectors to determine corresponding
classes for the additional vectors; and

generating an image using the feature vectors and the corresponding classes for the additional vectors.

US Pat. No. 9,109,979

Z-AXIS TEST COUPON STRUCTURE AND METHOD FOR ADDITIVE MANUFACTURING PROCESS

THE BOEING COMPANY, Chic...

1. A Z-axis test coupon structure, comprising:
a plurality of tensile specimens, each tensile specimen having a longitudinal axis, and the tensile specimens being circumferentially
space about a circle having a center on a first axis of the Z-axis test coupon structure such that the longitudinal axes of
the tensile specimens are parallel to the first axis;

and at least one web bridging a gap between adjacent ones of the plurality of tensile specimens to connect adjacent ones of
the plurality of tensile specimens.

US Pat. No. 9,064,357

VEHICLE DYNAMICS CONTROL USING INTEGRATED VEHICLE STRUCTURAL HEALTH MANAGEMENT SYSTEM

THE BOEING COMPANY, Chic...

1. A method for alleviating an anomaly in a structure, the method comprising:
embedding at least one anomaly detector structural member in the structure;
sending a measurement signal to the at least one anomaly detector structural member;
receiving a feedback signal from the at least one anomaly detector structural member in response to the measurement signal;
calculating in real-time a difference between the measurement signal and the feedback signal to determine a real-time change
in the structure;

identifying at least one non-optimal event in real-time if the real-time change exceeds an event threshold; and
altering in real-time dynamics control laws of a controller of the structure to control according to a new set of variables
based on the real-time change in the structure to provide updated dynamics control laws.

US Pat. No. 9,289,965

OPAQUE FIBER REINFORCEMENT OF COMPOSITES

THE BOEING COMPANY, Chic...

1. A method for reinforcing a composite material, comprising:
providing a first polymeric matrix resin;
providing transparent glass elements;
providing opaque elements;
embedding the transparent glass elements and the opaque elements in the polymeric matrix resin;
creating a prepreg;
forming a composite by laying up said prepreg using said transparent glass elements and said opaque elements; and
curing said composite.

US Pat. No. 9,180,960

BORON FIBER REINFORCED STRUCTURAL COMPONENTS

The Boeing Company, Chic...

1. A composite structural member system, comprising:
a plurality of composite structural members, each composite structural member including
a structural member core having
at least one diagonal interior fiber reinforced ply proximate to and orientated substantially diagonal to at least one of
the boron fiber reinforced plies, configured to define the structural member core,

at least one perpendicular interior fiber reinforced ply proximate to and orientated substantially perpendicular to at least
one of the boron fiber reinforced plies, configured to define the structural member core,

at least one parallel interior fiber reinforced ply proximate to and orientated substantially parallel to at least one of
the baron fiber reinforced plies, configured to define a structural member core, and

a plurality of boron fiber reinforced plies oriented in a substantially longitudinal direction, wherein the plurality of boron
fiber reinforced plies are disposed on each side of each of the at least one diagonal interior fiber reinforced ply, the at
least one perpendicular interior fiber reinforced ply and the at least one parallel interior fiber reinforced ply, and

at least one exterior fiber reinforced ply substantially surrounding the structural member core, configured to define a structural
member casing; and

an attachment ply layer encapsulating a substantial surface area of each of the composite structural members of the plurality
of composite structural members in the substantially longitudinal direction, a portion of the attachment ply layer extending
in a direction perpendicular to the at least one of the boron fiber reinforced plies towards adjacent composite structural
members.

US Pat. No. 9,394,148

LIFTING APPARATUS AND METHOD OF LIFTING

The Boeing Company, Chic...

1. A lifting apparatus, comprising:
a mobile base adapted to be supported by and moveable relative to a floor surface;
a lifting mechanism mounted to the mobile base;
suspension members for operatively engaging an object to be lifted, the suspension members extending from the lifting mechanism;
a counterweight system that is automatically moveable relative to the mobile base; and
a controller that receives load information based on a load of the object being lifted and adjusts the counterweight system
in response to the load information.

US Pat. No. 9,245,150

SEMANTICALLY DETERMINING A SECURITY CLASSIFICATION OF DATA

The Boeing Company, Chic...

1. A method for determining a security classification for data, the method comprising:
generating a classification signature for data based on a semantic interpretation of the data, the classification signature
associated with a security classification for the data, the data stored in a level of a security compartment corresponding
to the security classification for the data, the security compartment comprising one or more levels, wherein each level corresponds
to a particular security classification;

comparing the generated classification signature to a predetermined classification signature associated with the security
classification for the level of the security compartment where the data is stored;

verifying the generated classification signature matches the predetermined classification signature; and
monitoring data modifications and generating a classification signature for the data in real-time in response to the data
modifications;

wherein one or more classification recommendations for the data are presented to a user in response to the generated classification
signature for the data in real-time not matching the predetermined classification signature, a classification recommendation
comprising a data modification to conform the data to the security classification of the predetermined classification signature.

US Pat. No. 9,257,050

AIRPLANE POSITION ASSURANCE MONITOR

The Boeing Company, Chic...

1. A method for monitoring positional accuracy of an airplane approaching a runway, comprising the following steps performed
by a computer system during the approach:
(a) determining a ground distance between a location of the airplane and a touchdown aim point on the runway based on respective
coordinates thereof;

(b) determining a height of the airplane above a threshold of the runway based on an altitude of the airplane and an elevation
of a threshold of the runway;

(c) determining an angle between a hypothetical line extending from the airplane to the touchdown aim point and a perpendicular
projection of that line onto a locally level plane that passes through a runway threshold reference point based on the ground
distance and the height;

(d) determining a first vertical angular deviation of the airplane from a glideslope based on a difference of the determined
angle and a glide path angle;

(e) receiving a second vertical angular deviation of the airplane from the glideslope based on measurements of a difference
in a depth of modulation of first and second modulated signals transmitted from a ground-based antenna and received by an
antenna onboard the airplane;

(f) comparing the first and second vertical angular deviations; and
(g) generating an alert signal when the first and second vertical angular deviations differ by an amount greater than a threshold
value.

US Pat. No. 9,068,884

TURBULENCE AND WINDS ALOFT DETECTION SYSTEM AND METHOD

The Boeing Company, Chic...

1. A turbulence and winds aloft detection system, comprising:
an image capturing device for capturing a plurality of images of a visual feature of a selected celestial object; and
an image processor configured to
compare the plurality of images of the visual feature to detect a transit of a turbule of turbulent air between the image
capturing device and the selected celestial object;

compensate for one or more of apparent visual motion of celestial objects due to a planet's translation and rotation, the
moon's revolution about the planet, and the atmosphere's refractive displacement of celestial objects; and

compute a measurement of at least one of a velocity of the turbule and a height of the turbule relative to the planet.

US Pat. No. 9,266,687

SYSTEMS AND METHODS FOR DELIVERY OF DEVICES ALONG A TRANSPORT PATH

The Boeing Company, Chic...

1. A transport system comprising:
a transport tube having a feed end and a point of use end;
a plurality of fasteners;
a plurality of device carriers carrying the plurality of fasteners, wherein the plurality of device carriers comprises a common
external surface, and openings having different configurations to accommodate different configurations of heads of different
ones of the plurality of fasteners, at least some of the plurality of device carriers having a different internal configuration
than at least some of the other ones of the plurality of device carriers, the internal configuration determined based on at
least one physical characteristic of a fastener to be inserted therein; and

a source operable to move the plurality of device carriers through the transport tube from the feed end to the point of use
end, the plurality of device carriers having a common external surface to allow transport through the transport tube.

US Pat. No. 9,261,965

TOUCH SURFACE OVERLAY PANEL

THE BOEING COMPANY, Chic...

1. An overlay panel for an electronic device having a touch surface mounted within a housing, the overlay panel comprising:
a frame made of a nonconductive material;
one or more fasteners coupled to the frame, wherein the fasteners are configured to attach the frame to the housing of the
electronic device; and

one or more physical actuators mounted within the frame, each physical actuator having an upper portion that extends above
the frame and a lower portion that extends below the frame,

wherein the upper portion of each physical actuator is configured to be actuated by a user and the lower portion of each physical
actuator is configured to contact the touch surface when the frame is attached to the housing of the electronic device,

wherein each physical actuator comprises one or more conductive elements configured to create a conductive path from the upper
portion of each physical actuator to the lower portion of the physical actuator, and

wherein the one or more physical actuators mounted within the frame are aligned with virtual controls displayed on a touch
screen.

US Pat. No. 9,284,843

BLADE SAFETY MECHANISM FOR OPEN ROTOR ENGINE SYSTEM

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a blade connected to a hub in an open rotor engine system;
a conductor embedded within the blade and extending a length of an airfoil section of the blade; and
an activation system configured to allow electrical energy to flow into the conductor in response to an undesired blade event
such that the conductor vaporizes.

US Pat. No. 9,280,369

SYSTEMS AND METHODS OF ANALYZING A SOFTWARE COMPONENT

The Boeing Company, Chic...

1. A method comprising:
executing, based on a first set of operating conditions, a software component on a virtual machine executing at a computing
device;

monitoring kernel level events of an operating system executing on the virtual machine;
monitoring application level events of the operating system;
analyzing first effects of executing the software component on the virtual machine based on the kernel level events and the
application level events

determining an operating condition of the operating system to modify based on the first effects, wherein the operating condition
is determined by comparing the first effects to third effects associated with a database entry, and wherein the database entry
indicates the operating condition;

modifying the operating condition to generate a second set of operating conditions;
executing, based on the second set of operating conditions, the software component on the virtual machine; and
analyzing second effects of executing the software component with the second set of operating conditions based on monitored
second kernel level events and based on monitored second application level events.

US Pat. No. 9,276,476

FORCED COMMUTATING A CURRENT THROUGH A DIODE

THE BOEING COMPANY, Chic...

1. A method of eliminating reverse recovery time in a body diode of a field effect transistor (FET), the method comprising:
switching the FET on prior to force commutating a current into the body diode;
maintaining the FET on but not forcing the current into the body diode;
force commutating, while switching off the FET, the current from a cathode terminal of the body diode to an anode terminal
of the body diode; and

maintaining the FET off and not forcing the current into the body diode.

US Pat. No. 9,251,698

FOREST SENSOR DEPLOYMENT AND MONITORING SYSTEM

THE BOEING COMPANY, Chic...

1. A forestry management system comprising:
a forestry manager configured to:
receive information relating to a number of soil conditions for a location in a forest from a sensor system deployed by a
group of aerial vehicles and

identify a mission based on the number of soil conditions,
wherein the sensor system comprises sensor units having a housing and pins weighted such that the pins penetrate a ground
to generate the information from soil in the location;

wherein the pins include exposed portions and insulated portions such that the insulated portions localize measurements taken
by the exposed portions at a desired depth under a surface of the ground;

wherein moisture is determined based on a measurement of a resistance between the exposed portions of the pins;
wherein the insulated portions localize the measurement of the resistance at the desired depth under the surface of the ground;
wherein the pins include a temperature sensor; and
wherein the sensor units comprise at least one of recoverable sensor units or disposable soil sensor units, the disposable
soil sensor units configured to be deployed and not retrieved having housing comprised of material that is biodegradable.

US Pat. No. 9,205,933

AUTOMATED ASSEMBLY OF PANELIZED AIRCRAFT FUSELAGES

The Boeing Company, Chic...

1. A facility for assembling aircraft fuselages, the facility comprising:
a plurality of movable cradles, each of the movable cradles configured to support a fuselage keel structure; and
a movable gantry for loading fuselage keel structures on the cradles, and loading fuselage panels for each of the keel structures
to build up from each of the keel structures and assemble obtain a full fuselage contour in a single upright build position
without changing fuselage angular orientation.

US Pat. No. 9,297,708

METHODS AND SYSTEMS FOR OPTICAL WEAR SENSING

The Boeing Company, Chic...

1. A system comprising:
a medium operable to pass through a plurality of structural openings; and
a sensing system coupled to said medium, wherein said sensing system comprises:
a plurality of physical interfaces each positioned at locations where said medium passes through the plurality of structural
openings, said plurality of physical interfaces including a channel defined therethrough and at least one waveguide associated
therewith, wherein said at least one waveguide comprises a medium waveguide coupled to said medium, an interface waveguide
coupled to said physical interface, and a coupling waveguide coupled between said medium waveguide and said interface waveguide,
wherein said interface waveguide completely circumscribes said channel, said medium waveguide, said coupling waveguide, and
said interface waveguide configured to pass optical signals therethrough, wherein the ability to pass such optical signals
is indicative of monitoring of physical wear to said plurality of physical interfaces;

an emitter configured to channel the optical signals through said at least one waveguide;
a detector coupled in communication with said emitter, wherein said at least one waveguide is coupled between said emitter,
said plurality of physical interfaces, and said detector in series such that the optical signals from said emitter are detected
at said detector; and

an analysis unit coupled in communication with said detector, said analysis unit configured to determine physical wear to
said plurality of physical interfaces based on the optical signals received at said detector.

US Pat. No. 9,275,530

SECURE AREA AND SENSITIVE MATERIAL TRACKING AND STATE MONITORING

The Boeing Company, Chic...

1. A system for monitoring an area containing sensitive material, said system comprising:
an object comprising sensitive material, wherein said object is reactive to a predetermined condition, wherein subjection
to the predetermined condition neutralizes said sensitive material;

at least one radio frequency identification (RFID) tag coupled to said object and configured to change state when subjected
to the predetermined condition;

a reading and warning system comprising an RFID tag reader operable to receive a signal from said at least one RFID tag, wherein
said reading and warning system provides a warning when said at least one RFID tag is coupled to said object and said RFID
tag reader receives a signal from said at least one RFID tag, and

wherein said reading and warning system is configured to determine when the object is neutralized based on at least one of:
receiving an altered signal from said at least one RFID tag when said RFID tag changes state, or receiving no signal from
said at least one RFID tag when said RFID tag changes state.

US Pat. No. 9,257,048

AIRCRAFT EMERGENCY LANDING ROUTE SYSTEM

THE BOEING COMPANY, Chic...

1. A method for managing a landing site for an aircraft, the method comprising:
selecting, using a navigation tool, the landing site from a group of landing sites;
determining, using a routing tool, a touchdown point on the landing site;
growing, using the routing tool, a spanning tree comprising a minimum cost path up from the touchdown point to an origin point
in the air;

computing, using the routing tool, a route from a current location of the aircraft to the origin point, the route being four-dimensional;
communicating, to a platform, a description of a state of the aircraft along the route of the aircraft over time to the landing
site; and

flying the aircraft to the landing site using the description of the state of the aircraft along the route of the aircraft
over time.

US Pat. No. 9,250,051

SQUIB INITIATION SEQUENCER

The Boeing Company, Chic...

1. A method for sequentially initiating a plurality of squibs in one or more release mechanisms, the method comprising:
firing a first squib and a second squib of the plurality of squibs at the same time by passing a current generated by a power
source through the first squib and the second squib;

in response to determining that the current through the first squib is below a minimum threshold amount, disconnecting the
first squib from the power source; and

in response to determining that the current through the first squib and a current through the second squib are both below
the minimum threshold amount, firing a third squib of the plurality of squibs.

US Pat. No. 9,276,156

SOLAR CELLS HAVING A TRANSPARENT COMPOSITION-GRADED BUFFER LAYER

The Boeing Company, Chic...

1. A solar cell comprising:
a first layer having a first-layer lattice parameter;
a second layer having a second-layer lattice parameter different from the first-layer lattice parameter, wherein the second
layer includes a photoactive second-layer material; and

a buffer layer extending between and contacting the first layer and the second layer and having a buffer-layer lattice parameter
that increases with increasing distance from the first layer toward the second layer,

wherein the first layer is transparent to wavelengths of light that are photoconverted by the second layer; and
wherein the buffer layer is made of a buffer-layer material having a minimum bandgap greater than a bandgap of the second
layer by at least 50 milli-eV.

US Pat. No. 9,488,067

AIRCRAFT ANTI-ICING SYSTEMS HAVING DEFLECTOR VANES

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a skin on an inlet side of a nacelle of an aircraft defining an annular chamber;
a gas delivery system including a nozzle disposed within the annular chamber, the nozzle to provide a first gas to mix with
and entrain a second gas in the annular chamber to define a flow through the annular chamber, wherein the second gas is at
a different temperature from the first gas; and

a deflector vane disposed within the annular chamber and in a direct impingement flow path of the nozzle, the deflector vane
to redirect the flow through the annular chamber to increase a flow path length of the flow through the annular chamber.

US Pat. No. 9,386,694

SUPER LIGHT WEIGHT ELECTRONIC CIRCUIT AND LOW POWER DISTRIBUTION IN AIRCRAFT SYSTEMS

The Boeing Company, Chic...

1. A method for applying conductive traces to a structure to complete an electrical circuit, comprising the steps of:
forming one or more graphene traces on a substrate; and
applying the substrate to the structure such that one or more first portions of the electrical circuit are electrically connected
to respective one or more second portions of the electrical circuit by respective ones of the one or more graphene traces.

US Pat. No. 9,369,868

SYSTEM AND METHOD FOR SECURE WIRELESS COMMUNICATIONS BETWEEN A VEHICLE AND A SOURCE

The Boeing Company, Chic...

1. A system for secure wireless communications comprising:
a first wireless communication device configured to be disposed on a vehicle and comprising a first signal amplifier configured
to amplify a data signal transmitted by the first wireless communication device;

a second wireless communication device configured to be disposed on a source and to wirelessly communicate data with the first
wireless communication device, the second wireless communication device comprising a second signal amplifier configured to
amplify a second data signal transmitted by the second wireless communication device;

at least one information device configured to provide information regarding the vehicle or the source;
at least one processor in electronic communication with the at least one information device; and
at least one memory in electronic communication with the at least one processor, wherein the at least one memory comprises
programming code for execution by the at least one processor, and the programming code is configured to only activate the
first signal amplifier and the second signal amplifier when security parameters, stored in the at least one memory, are satisfied
by both the vehicle and the source, based on the information provided by the at least one information device, in order to
facilitate wireless communications of the data between the first wireless communication device and the second wireless communication
device.

US Pat. No. 9,283,706

METHOD AND APPARATUS FOR COMPRESSION MOLDING FIBER REINFORCED THERMOPLASTIC PARTS

THE BOEING COMPANY, Chic...

1. A method of compression molding an elongated fiber reinforced thermoplastic part, comprising:
pre-consolidating a quantity of fiber reinforced thermoplastic resin flakes into a mold charge, wherein the step of pre-consolidating
the quantity of fiber reinforced thermoplastic resin flakes further comprises: placing the quantity of fiber reinforced thermoplastic
resin flakes into a chamber, wherein the fiber reinforced thermoplastic resin flakes have a generally oval shape such that
fibers of the fiber reinforced thermoplastic resin flakes have varying lengths of between approximately 0.5 inches and approximately
1.0 inches; heating a number of electrical resistance coils integrated into ceramic band heaters sleeved over the chamber
to a melting temperature of a resin in the fiber reinforced thermoplastic resin flakes, and compacting the fiber reinforced
thermoplastic resin flakes in the chamber into the mold charge;

loading the mold charge into a charge cylinder;
heating the charge cylinder until the mold charge is flowable;
heating a mold, wherein the mold comprises a part cavity and at least one fitting cavity;
injecting the flowable mold charge into the heated mold to mold the mold charge into the part, wherein the step of injecting
the flowable mold charge into the heated mold further comprises: injecting the flowable mold charge into the heated mold to
mold the mold charge into the part to achieving a uniform distribution of the fibers of varying lengths in the part, wherein
the uniform distribution promotes isotropic mechanical properties and strengthens the part; and

cooling the mold until the part is capable of retaining its shape.

US Pat. No. 9,159,487

LINEAR ELECTROMAGNETIC DEVICE

The Boeing Company, Chic...

1. A linear electromagnetic device, comprising:
a core in which a magnetic flux is generable;
an opening through the core, wherein the opening through the core comprises an elongated slot; and
a plurality of primary conductors received in the opening and extending through the core, each primary conductor including
a substantially square or rectangular cross-section and are each disposed directly adjacent one another in a single row in
the elongated slot, the elongated slot comprising two elongated side walls connected at each end by an end wall, each primary
conductor including a predetermined width in a direction corresponding to the elongated side walls and each end primary conductor
being less than about one half of the predetermined width from a respective one of the side walls, wherein only the primary
conductors and no other conductors extend through the elongated slot in the core and wherein an electrical current flowing
in one direction through the primary conductors generates a magnetic field about the primary conductors, substantially the
entire magnetic field being absorbed by the core to generate the magnetic flux in the core.

US Pat. No. 9,284,068

FAST-LOW ENERGY TRANSFER TO EARTH-MOON LAGRANGE POINT L2

The Boeing Company, Chic...

1. A control system for a hybrid propulsion spacecraft configured for transfer between low earth parking orbit (LEO) and a
Lissajous L2 orbit (L2O), the control system comprising:
a first control portion communicably connected to a high thrust (HT) engine portion of the hybrid propulsion spacecraft;
a second control portion communicably connected to a low thrust high specific impulse (LT-HI) engine portion of the hybrid
propulsion spacecraft; and

the first and second control portions being configured to control both the HT engine portion and the LT-HI engine portion
of the hybrid propulsion spacecraft to provide an optimal LEO to L2O transfer trajectory;

wherein the optimal LEO to L2O trajectory includes an optimal LT-HI trajectory portion, selected from a stable manifold trajectory,
and an optimal HT trajectory portion, and wherein the LT-HI trajectory portion and HT trajectory portion are configured for
providing a combined optimal trajectory along the LEO to L2O transfer trajectory, and are optimized substantially simultaneously.

US Pat. No. 9,283,598

METHODS, SYSTEMS, AND DEVICES FOR RADIO-FREQUENCY ASSISTED REMOVAL OF SEALANT

The Boeing Company, Chic...

1. A method of sealing a fuel tank within an aircraft, the method comprising:
sealing the fuel tank with sealant by applying a first quantity of uncured sealant to the fuel tank and by curing the first
quantity of uncured sealant to form a first cured sealant;

inspecting the first cured sealant in the fuel tank to determine if the fuel tank is properly sealed; and
determining that the fuel tank is not properly sealed;
exposing a volume of the first cured sealant to microwave radiation, sufficient to heat a susceptor within the volume to form
a reduced bond-strength sealant;

physically removing the reduced bond-strength sealant; and
sealing the fuel tank with sealant by applying a second quantity of uncured sealant to the fuel tank and by curing the second
quantity of uncured sealant to form a second cured sealant.

US Pat. No. 9,221,533

REMOVABLE WINDOW SYSTEM FOR SPACE VEHICLES

THE BOEING COMPANY, Chic...

1. A window system for a platform, the window system comprising:
a window pane configured to contact a sealing system;
a retention frame configured to contact the sealing system and hold the window pane against a support frame; and
a biasing system configured to bias the retention frame toward the support frame while the support frame and the retention
frame are in a configuration that holds the window pane, and removal of the biasing system causes the retention frame and
the window pane to be removable;

wherein a first portion of the biasing system is configured to contact the retention frame and a second portion of the biasing
system is configured to engage a channel in the support frame.

US Pat. No. 9,283,711

HYBRID ABLATIVE THERMAL PROTECTION SYSTEMS AND ASSOCIATED METHODS

The Boeing Company, Chic...

1. A method of forming a thermal protection system for high speed aircraft comprising:
mechanically working a first amount of uncured, silicone-based ablator material into a first surface of a felt layer such
that the ablator material penetrates a distance into a thickness of the felt layer thereby forming a region in the felt layer
exposed at the first surface that has a mixture of felt and ablator material;

adding a second amount of uncured, silicone-based ablator material to the first surface across the worked ablator material
at the region formed in the felt layer such that the first and second amounts of uncured, silicone-based ablator material
are combined; and

curing the combined ablator material.

US Pat. No. 9,248,326

SCALABLE CARGO FIRE-SUPPRESSION AGENT DISTRIBUTION SYSTEM

The Boeing Company, Chic...

1. A method for scaling cargo fire-suppression agent distribution, comprising:
detecting an operation condition;
selecting a supply source unit subset of a set of fire-suppression agent supply source units to provide a selected supply
source unit subset if the operation condition indicated a descent;

discharging a fire-suppressant agent at a discharge rate directly from the selected supply source unit subset into a vehicle
ducting; and

distributing the fire-suppression agent into a contained volume at the discharge rate from the selected supply source unit
subset during the descent.

US Pat. No. 9,169,521

POINT-OF-COLLECTION SAMPLE PREPARATION DEVICE AND METHOD

The Boeing Company, Chic...

1. An analyte detection device, the device comprising:
a multilayer member configured to receive a fluid-borne sample comprising at least one analyte in combination with one or
more non-analyte components, the multilayer member comprising at least:

a sample preparation layer comprising consecutive filter layers of a cell lysis layer and a concentrating layer, both configured
to dissolve upon receiving at least a portion of the fluid-borne sample to produce a solution comprising at least a portion
of the fluid-borne sample; and

an analysis cartridge in microfluidic communication with the multilayer member, the analysis cartridge configured to determine
a presence and/or a concentration of the analyte in the solution and

a microfluidic system providing microfluidic communication between the sample preparation layer and the analysis cartridge,
the microfluidic system comprising at least one of: a capillary tube; an electro-osmatic pump contact in communication with
a capillary tube; or a heater in thermal communication with a capillary tube.

US Pat. No. 9,266,389

WHEEL SYSTEM FOR A VEHICLE

The Boeing Company, Chic...

1. A wheel assembly for use with a vehicle, said wheel assembly comprising:
a first inner wheel portion comprising a first plurality of walls that combine to define a substantially hollow first chamber;
a second inner wheel portion positioned adjacent to said first inner wheel portion, said second inner wheel portion comprising
a second plurality of walls that combine to define a substantially hollow second chamber;

a first wheel bladder comprising a first radially inner wall coupled to a radially outer wall of said first plurality of walls
such that said first wheel bladder is positioned radially outward from said first inner wheel portion, said first chamber
configured to induce suction, pressure, or both to said first wheel bladder; and

a second wheel bladder comprising a second radially inner wall coupled to a radially outer wall of said second plurality of
walls such that said second wheel bladder is positioned radially outward from said second inner wheel portion, wherein the
wheel assembly is coupled to an axle assembly including an inner axle and an outer axle configured to rotate about the inner
axle, the inner axle configured to retain an inflation device for inducing at least one of suction and pressure to the wheel
assembly.

US Pat. No. 9,132,921

REFUELING BOOM CONTROL SYSTEM

THE BOEING COMPANY, Chic...

1. A method for moving a refueling boom on a tanker aircraft, the method comprising:
receiving a number of operator commands for moving the refueling boom on the tanker aircraft in a desired direction, wherein
the number of operator commands defines at least one of an azimuth movement and an elevation movement of the refueling boom
during flight of the tanker aircraft; and

generating a number of intermediate commands for moving the refueling boom in the desired direction as defined by the number
of operator commands, wherein the number of intermediate commands defines at least one of a roll movement and a pitch movement
such that the refueling boom moves in the desired direction;

wherein the operator commands include an operator azimuth command and an operator elevation command; and wherein the roll
movement and the pitch movement result in substantially linear azimuth movement of the refueling boom from the operator azimuth
command and substantially linear elevation movement of the refueling boom from the operator elevation command.

US Pat. No. 9,485,849

RF PARTICLE ACCELERATOR STRUCTURE WITH FUNDAMENTAL POWER COUPLERS FOR AMPERE CLASS BEAM CURRENT

The Boeing Company, Chic...

1. A radio frequency particle accelerator structure, comprising:
a first electromagnetic resonant cavity operable to drive a particle beam by resonating an electromagnetic mode, wherein the
first electromagnetic resonant cavity has a first end and a second end;

a second electromagnetic resonant cavity sequentially coupled to the first electromagnetic resonant cavity, and operable to
drive the particle beam by resonating the electromagnetic mode, wherein the second electromagnetic resonant cavity has a first
end and a second end;

a beam pipe directly connecting the second end of the first electromagnetic resonant cavity and the first end of the second
electromagnetic cavity;

a first fundamental power coupler directly coupled to the first end of the first electromagnetic resonant cavity and operable
to emit radio frequency electromagnetic energy into the first end of the first electromagnetic resonant cavity; and

a second fundamental power coupler located in the beam pipe and operable to emit radio frequency electromagnetic energy into
the second end of the first electromagnetic resonant cavity and the first end of the second electromagnetic resonant cavity.

US Pat. No. 9,285,296

SYSTEMS AND METHODS FOR STAND-OFF INSPECTION OF AIRCRAFT STRUCTURES

The Boeing Company, Chic...

1. A system comprising:
a support;
a pan-tilt mechanism mounted to said support;
an assembly mounted to said pan-tilt mechanism, said assembly comprising a camera and a nondestructive evaluation instrument
which are affixed to each other; and

a computer system programmed to execute the following operations:
(a) controlling said pan-tilt mechanism to determine a direction vector to a target object;
(b) controlling said camera to acquire image data representing an image of an area on a surface of the target object which
is intersected by the direction vector;

(c) processing the image data to determine whether the image of the area includes information indicating presence of an anomaly
in the area;

(d) if it is determined in operation (c) that the image data includes information indicating the presence of an anomaly in
the area, determining coordinates of a position of the anomaly relative to a coordinate system of the target object based
on the image data;

(e) controlling said pan-tilt mechanism to direct said nondestructive evaluation instrument toward an area on the target object
having said coordinates; and

(f) controlling said nondestructive evaluation instrument to acquire nondestructive evaluation measurement data from said
area on the target object having said coordinates using a stand-off nondestructive evaluation technique.

US Pat. No. 9,262,939

INTEGRATED LIVE AND SIMULATION ENVIRONMENT SYSTEM FOR AN AIRCRAFT

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
an aircraft;
a network interface associated with the aircraft, wherein the network interface is configured to exchange data using a wireless
communications link;

a display system associated with the aircraft;
a sensor system associated with the aircraft;
a computer system at a ground-based location remote from the aircraft, the computer system in communication with the network
interface, the computer system configured to perform a simulation of a first number objects and generate first simulation
data from the simulation and send the first simulation data to the network interface, such that the first simulation data
comprises virtual data; and

a training processor within the aircraft, such that the training processor is configured to:
receive the first simulation data;
convert the first simulation data to a format matching live sensor data;
generate constructive data for a number of simulation objects using the first simulation data;
generate simulation sensor data using the constructive data and the virtual data; and
present the simulation sensor data with live sensor data generated by the sensor system on the display system, the simulation
sensor data including a model of a sensor in the sensor system such that the model comprises at least: a radar model that
simulates operation of a radar system in the aircraft, and a radar warning receiver model that simulates operation of a radar
warning receiver in the aircraft, such that the training processor provides the constructive data and the simulation sensor
data to an aircraft network of the aircraft, the aircraft network linked to a second computer system of the aircraft; and

the second computer system comprises the display system, and the display system comprises one or more display devices.

US Pat. No. 9,278,849

MICRO-SENSOR PACKAGE AND ASSOCIATED METHOD OF ASSEMBLING THE SAME

The Boeing Company, Chic...

1. A micro-sensor package comprising:
a micro-sensor comprising:
a first substrate having opposing front and back surfaces;
a sensing element on the front surface of the first substrate; and
a through-chip via disposed within the first substrate and electrically connected to the sensing element;
a printed circuit board including a second substrate with a front surface to which the back surface of the first substrate
is bonded, the second substrate defining a recess within which a bond pad is disposed, the bond pad being disposed within
the recess below the front surface of the second substrate such that the recess has an open volume above the bond pad, the
through-chip via of the micro-sensor being electrically connected to the bond pad of the printed circuit board; and

a shim surrounding an outer boundary of the micro-sensor and bonded to the printed circuit board, the shim having approximately
the same thickness as the micro-sensor.

US Pat. No. 9,281,108

CLAMP ASSEMBLY INCLUDING PERMANENT MAGNETS AND COILS FOR SELECTIVELY MAGNETIZING AND DEMAGNETIZING THE MAGNETS

The Boeing Company, Chic...

1. A method of clamping a stack, the method comprising:
positioning permanent magnets against a first surface of the stack;
placing a flux-conducting structure against a second surface of the stack; and
applying external magnetic field pulses to the permanent magnets to magnetize and demagnetize the permanent magnets,
wherein applying external magnetic field pulses to the permanent magnets to magnetize the permanent magnets comprises promoting
magnetic domain alignment within the permanent magnets sufficient to clamp the stack between the permanent magnets and the
flux conducting structure;

wherein applying external magnetic field pulses to the permanent magnets to demagnetize the permanent magnets comprises demoting
magnetic domain alignment within the permanent magnets sufficient to reduce a clamping force applied to the stack by the flux-conducting
structure and the permanent magnets;

wherein applying external magnetic field pulses is performed in a first direction for magnetizing the permanent magnets; and
wherein applying external magnetic field pulses is performed in a second direction for demagnetizing the permanent magnets,
the second direction being opposite the first direction.

US Pat. No. 9,272,312

METHODS AND SYSTEMS FOR REMOVING LUBRICANTS FROM SUPERPLASTIC-FORMING OR HOT-FORMING DIES

The Boeing Company, Chic...

9. A method of cleaning a die, the method comprising:
analyzing a working surface of the die with an analyzing device to determine a thickness of a layer of at least one of graphite
and boron nitride thereon; and

based on the thickness of the layer, discharging electromagnetic energy from an electromagnetic-energy emission device (EEED)
to irradiate the surface of the die with the electromagnetic energy, wherein the electromagnetic energy ablates the at least
one of graphite and boron nitride such that the electromagnetic energy removes the layer without removing an oxide layer between
said working surface and said layer.

US Pat. No. 9,277,037

PORTABLE COMMUNICATION DEVICES WITH ACCESSORY FUNCTIONS AND RELATED METHODS

The Boeing Company, Chic...

1. An accessory module for providing at least one accessory function to a portable communication device, the portable communication
device including a processor and an interface connector, the interface connector disposed on a back side of a housing of said
portable communication device such that the interface connector is positioned behind a removable back panel when coupled to
the housing, said accessory module comprising:
an accessory module back panel;
a means for providing at least one accessory function;
a module connector configured to mate with the interface connector of the portable communication device; and
a means for coupling said accessory module back panel to the housing in place of the removable back panel of the portable
communication device when the removable back panel is uncoupled from the housing, said module connector positioned on said
accessory module back panel such that said module connector mates with the interface connector when said accessory module
back panel is secured to the housing, and such that said accessory module is coupled to the portable communication device
and communicates with the processor of the portable communication device via said module connector to provide said at least
one accessory function.

US Pat. No. 9,157,260

HYDRAULICALLY ACTUATED LATCH MECHANISM

The Boeing Company, Chic...

1. A storage system comprising:
a storage compartment having a compartment door;
a plurality of latches for latching the door, the latches being closed by the door;
a plurality of slave cylinders coupled to the latches; and
a master cylinder in fluid communication with the slave cylinders for causing the slave cylinders to simultaneously open the
latches but not to close the latches.

US Pat. No. 9,275,198

SYSTEMS AND METHODS FOR ELECTRONICALLY PUBLISHING CONTENT

THE BOEING COMPANY, Chic...

1. A method, comprising:
receiving a selection of content in response to displaying a first selectable option on a first user interface to enable the
content to be identified or selected;

receiving a selection of rights assigned to the content in response to displaying a second selectable plurality of options
on a second user interface, the second selectable options designating different rights to be associated with the content upon
selection, the rights assigned to be associated with one or more groups to be granted access to the content, the rights assigned
to enable a security trimmed search return;

receiving a selection of one or more tags in response to displaying a third selectable plurality of options on a third user
interface, the third selectable options corresponding to different tags to be associated with the content upon selection,
the third selectable options including different control tags, different supplier tags, and different regulations associated
with the content, in response to the selection of one or more of the third selectable options, the one or more tags are assigned
to the content to enable at least one of content delivery, content identification, or content searchability, the tags are
associated with one or more of the different regulations, one or more of the different supplier tags, or one or more of the
different control tags, the one or more tags to enable a rank adjusted search return, the rights assigned are different than
the one or more tags;

directly associating the content with the rights assigned and the one or more tags to enable a security trimmed rank adjusted
search return of the content;

scanning the content and, in response to and based on the scanned content, generating a first content associated identifier,
the first content associated identifier uniquely identifying the content;

comparing the first content associated identifier to other content associated identifiers, the other content associated identifiers
being associated with previously published content, the other content associated identifiers uniquely identifying respective
portions of the previously published content, the comparing to determine if the first content associated identifier is substantially
the same as one of the other content associated identifiers to determine that the content has not been published previously;
and

in response to determining that the content has not been published previously, publishing the content.

US Pat. No. 9,272,362

FRICTION STIR WELD PLUGS AND METHODS OF USING THEREOF

The Boeing Company, Chic...

1. A method of friction stir welding an object, the method comprising:
performing a first friction stir weld along a first weld path having an exit,
wherein an opening is formed in the object at the exit;
installing a plug into the opening,
wherein:
the plug is consolidated in the opening by deforming a flange of the plug toward a body of the plug and is rotationally and
translationally secured in the opening upon installation,

the flange contacts the body after installation,
the flange is a second flange,
a first flange of the plug is in contact with the body and extends away from the body; and
the second flange shears from the first flange and consolidates into a gap toward the body upon installation; and
performing a second friction stir weld along a second weld path traversing the opening that contains the plug installed therein,
wherein the plug is at least partially consumed in the second friction stir weld.

US Pat. No. 9,272,495

COMPACTION SYSTEM FOR COMPOSITE STRINGERS

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a compacting structure having:
a first surface;
a second surface having a shape of one side of a composite stringer, wherein the first and second surface form an enclosure
structure when the compacting structure is placed against a mold;

a first opening in the first surface; and
a number of second openings in the second surface;
a compactor vacuum system associated with the first opening of the compacting structure, wherein the compactor vacuum system
is configured to cause a vacuum in the enclosure structure and apply a pressure to layers of uncured composite material when
a compactor vacuum is applied to the compactor vacuum system; and

a carrier vacuum system associated with the number of second openings in the second surface, wherein the carrier vacuum system
holds the layers of uncured composite material against the compacting structure while the compacting structure is positioned
and placed against the mold when a carrier vacuum is applied to the carrier vacuum system.

US Pat. No. 9,250,099

PREDICTING AIRCRAFT TRAJECTORY

THE BOEING COMPANY, Chic...

1. A method of predicting a trajectory of an aircraft and operating the aircraft, comprising:
receiving, at a processor, information defining how the aircraft is to be flown during an operation interval, and storing
the information in an information database;

deriving, by the processor, a set of instructions from the information stored, wherein the set of instructions comprise configuration
instructions that describe an aerodynamic configuration of the aircraft and motion instructions that control an aircraft motion,
wherein the aerodynamic configuration comprises a physical configuration of at least one of a high lift device of the aircraft,
a landing gear of the aircraft, and a speed brake of the aircraft;

confirming, by the processor, that the set of instructions comply with a set of rules stored in a rules database, that the
configuration instructions define the aerodynamic configuration of the aircraft and that the motion instructions close degrees
of freedom of equations of motion used to describe the aircraft motion during the operation interval;

thereafter formulating, by the processor using the set of instructions, an aircraft intent;
solving, by the processor, a trajectory optimization problem defined by the aircraft intent according to a predefined criterion
to obtain an optimized trajectory; and

operating the aircraft according to the optimized trajectory.

US Pat. No. 9,290,260

WING FOLD CONTROLLER

THE BOEING COMPANY, Chic...

1. A method of controlling folding of a wing, the method comprising:
receiving, in a wing fold controller, a status of at least one of: an aircraft, a wing fold system, such that the aircraft
comprises the wing fold controller and the wing fold system;

receiving, in the wing fold controller, a command in response to receiving the status;
operating the wing fold system, using the wing fold controller, based on the command and the status;
determining, via the wing fold controller, if a lock of the wing fold system is operational via attempting to move a wingtip
via a wingtip actuator after the lock of the wing fold system is in an engaged position; and

communicating a warning in response to attempting to move the wingtip after the lock is in the engaged position.

US Pat. No. 9,277,554

SERVERS AND METHODS FOR OPERATING A COMMUNICATION SYSTEM

The Boeing Company, Chic...

1. A server comprising:
a memory device configured to store a plurality of computer-executable instructions; and
a processor coupled to said memory device, wherein, when said processor executes the plurality of computer-executable instructions,
said processor is programmed to:

determine an available spectrum of frequencies within a location over time, the determination made by determining a geospatial
usage of the spectrum relative to time based on an expected spectrum usage over time by at least one registered device authorized
to use the spectrum, a measured or estimated usage of the spectrum over time by at least one unregistered device, and a historical
usage of the spectrum at the location;

receive a request from a wireless device to access the available spectrum for a predefined duration at a first level of service;
determine whether sufficient spectrum is available to enable the wireless device to operate at the first level of service;
determine whether sufficient spectrum is available to enable the wireless device to operate at a second level of service that
is lower quality than the first level of service upon a determination that sufficient spectrum is not available to enable
the wireless device to operate at the first level of service;

select a frequency band within the spectrum that is available to be used by the wireless device for the predefined duration
at the first or second level of service; and

transmit an authorization message commanding the wireless device to use the selected frequency band.

US Pat. No. 9,248,613

METHOD FOR FORMING THICK THERMOPLASTIC COMPOSITE STRUCTURES

THE BOEING COMPANY, Chic...

1. A method of making a thick thermoplastic composite part, comprising:
assembling a ply stack including a plurality of thermoplastic composite plies into a generally flat, unshaped condition;
pre-consolidating the ply stack in the generally flat, unshaped condition, including softening the plies by heating the plies
in the ply stack to a pre-consolidation temperature below the melting temperature of the thermoplastic, maintaining the ply
stack at pre-consolidation temperature over a pre-consolidation dwell time, and compressing the ply stack at the pre-consolidation
temperature by applying pressure to the plies sufficient to de-bulk the ply stack over the pre-consolidation dwell time;

subsequent to pre-consolidating the ply stack over the pre-consolidation dwell time, pre-forming the pre-consolidated ply
stack at a temperature below the melting temperature of the thermoplastic, including preforming at least one feature in the
pre-consolidated ply stack such that the pre-formed ply stack takes a general shape of a final part; and

consolidating the pre-formed ply stack, including heating the ply stack to at least the melting temperature of the thermoplastic.

US Pat. No. 9,510,398

INDUCTION HEATING APPARATUS

The Boeing Company, Chic...

1. A heating apparatus comprising:
a container including a side wall and a bottom wall, the side wall defining a length between an upper edge and a lower edge;
a plurality of first susceptor wires embedded in the side wall of the container and radially spaced relative to a center axis
of the container, each first susceptor wire includes an elongate body defining a first longitudinal axis, the first longitudinal
axis of each first susceptor wire is substantially parallel relative to the center axis such that a first end of each first
susceptor wire is adjacent the upper edge of the side wall and a second end of each first susceptor wire is adjacent a lower
edge of the side wall, each first susceptor wire being composed of a first material having a relatively high magnetic permeability
and a first Curie temperature characteristic, each first susceptor wire including a first outer surface extending along the
first longitudinal axis, and a first core within the first outer surface and extending along the first longitudinal axis,

a plurality of first conductor wires embedded in the side wall of the container, a respective one of the first conductor wires
being wrapped about a corresponding respective one of the first susceptor wires, the respective one of the first conductor
wires to receive electrical current from a power source to generate a corresponding respective first magnetic field, the corresponding
respective first magnetic field to generate eddy currents circumferentially adjacent the first outer surface of the corresponding
respective first susceptor wire when a temperature of the corresponding respective first susceptor wire is below the first
Curie temperature characteristic and to generate eddy currents adjacent the first core of the corresponding respective first
susceptor wire when the temperature of the corresponding respective first susceptor wire is equal to the first Curie temperature
characteristic.

US Pat. No. 9,359,067

METHOD OF FLYING AN UNMANNED AERIAL VEHICLE

THE BOEING COMPANY, Chic...

1. A method of flying an unmanned aerial vehicle, the method including steps implemented using a controller forming part of
the unmanned aerial vehicle, said steps comprising:
defining a plurality of emergency conditions;
associating each emergency condition of the plurality of emergency conditions with a corresponding priority level;
associating the each emergency condition with a corresponding objective;
sensing a plurality of operating parameters of the unmanned aerial vehicle to detect whether one of the plurality of emergency
conditions exists;

when one or more emergency conditions is detected:
generating a trajectory for a particular emergency condition having a highest associated priority level, wherein the trajectory
is generated in accordance with a particular objective associated with the particular emergency condition that has the highest
associated priority level; and

instructing the unmanned aerial vehicle to follow the trajectory.

US Pat. No. 9,180,961

CONTROL SURFACE FOR CREATING VARIABLE CAMBER ALONG A WING

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a control surface associated with a portion of an aft edge of a wing, wherein the control surface comprises:
a plurality of segments in which each of the plurality of segments comprises a number of sections; and
a shaping system associated with the control surface and configured to move each segment in the plurality of segments independently
of other segments in the plurality of segments to control a shape of an outer surface of the control surface, such that each
segment comprises a number of section mechanisms, such that each of the number of section mechanisms is configured to move
a corresponding section in the number of sections independently of other sections in the number of sections.

US Pat. No. 9,276,951

SYSTEM AND METHOD FOR DISCOVERING OPTIMAL NETWORK ATTACK PATHS

THE BOEING COMPANY, Chic...

1. A computer-implemented method for discovering network attack paths comprising:
generating scoring system results, using a computer, based on analysis of vulnerabilities of nodes in a network configuration,
wherein the scoring system results are a quantitative assessment of severities of computer system security vulnerabilities
of the nodes in the network;

applying, using the computer, a Bayesian probability model to the scoring system results to provide probabilities of attack
paths into the network, wherein the Bayesian probability model includes conditional dependency probability tables reflecting
dependencies between risks associated with different nodes in the network;

combining, using the computer, qualitative input with both the scoring system results and the probabilities of attack paths,
wherein by combining an output is formed, wherein the qualitative input comprises selected qualitative risk attributes that
comprise at least one of threat type, ease of execution, business risk, and certification risk;

accounting, using the computer, for betweenness centrality of nodes as a risk factor, wherein betweeness centrality quantifies
a number of times a given node in the network acts as a bridge along a shortest path between two other nodes in the network;
and

accounting, using the computer, for assortativity of nodes, wherein assortativity represents a preference for a given node
in the network to attached to other nodes in the network; and

applying, using the computer, a weighted-average algorithm to the output to yield at least one ranking of nodes in order of
likelihood of targeting by an external attacker.

US Pat. No. 9,359,061

COMPLIANT STIFFENER FOR AIRCRAFT FUSELAGE

The Boeing Company, Chic...

1. An aircraft fuselage nose section having a longitudinal axis, and comprising:
a unitary circumferentially extending composite skin;
a plurality of composite fiber stiffeners;
each stiffener including at least one foot, at least one sidewall, and a cap,
the at least one foot bonded to an interior circumference of the composite skin,
each stiffener extending in a circumferential direction,
said plurality of composite fiber stiffeners spaced orthogonally with respect to the longitudinal axis to define a spaced
parallel array,

each stiffener defining a continuous circumferential structural component of the nose section,
the cap spaced apart from the skin;
wherein the cap includes plies of carbon fibers that extend at an angle with respect to the circumferential direction;
wherein the cap further includes plies of glass fibers that extend orthogonally with respect to the longitudinal axis; and
wherein the interior circumference of the composite skin is stringerless.

US Pat. No. 9,199,713

PRESSURE PANELS

The Boeing Company, Chic...

1. An aircraft, comprising:
a fuselage with a pressurized compartment;
a wing assembly including outboard wing sections and a wing center section between the outboard wing sections; and
at least one pressure panel including:
a body having a width defining a lateral direction, a length defining a longitudinal direction, and a thickness that is substantially
less than the width and the length, wherein the body is a monolithic body;

wherein the body has a first region that substantially spans the width of the body, and a second region that substantially
spans the width of the body;

wherein the first region yields to lateral deformation more than the second region;
wherein the body defines a first plurality of elongated beads within the first region; and
wherein the body defines a second plurality of elongated beads within the second region;
wherein the at least one pressure panel is supported by the fuselage and is configured to at least partially maintain a pressure
within the pressurized compartment that is greater than or less than a pressure outside of the aircraft while the aircraft
is in flight; and

wherein the at least one pressure panel is positioned with the first region adjacent to and in mechanical communication with
the wing center section.

US Pat. No. 9,544,998

GROWTH OF CARBON NANOTUBE (CNT) LEADS ON CIRCUITS IN SUBSTRATE-FREE CONTINUOUS CHEMICAL VAPOR DEPOSITION (CVD) PROCESS

THE BOEING COMPANY, Chic...

1. A method for forming a plurality of electrical circuits, comprising:
forming a first carbon nanotube (CNT) catalyst layer comprising a plurality of first CNT catalyst plugs over a release layer;
forming a plurality of electrical circuits over the first CNT catalyst layer, wherein each electrical circuit is in electrical
communication with the first CNT catalyst layer;

forming a second CNT catalyst layer comprising a plurality of second CNT catalyst plugs over the plurality of electrical circuits,
wherein each electrical circuit is in electrical communication with the second CNT catalyst layer;

removing the release layer to expose the plurality of first CNT catalyst plugs; and
simultaneously forming a plurality of CNTs on the plurality of first CNT catalyst plugs and on the second plurality of CNT
catalyst plugs within a chamber of a reactor.

US Pat. No. 9,750,162

INTERCHANGEABLE INTERNAL MODULAR AVIONICS PLATFORM ASSEMBLY

The Boeing Company, Chic...

1. An interchangeable modular avionics platform assembly, comprising an interchangeable modular avionics platform including:
a frame structure having substantially parallel opposing side portions spaced apart at a predetermined width so that the frame
structure fits between opposing airframe members within a forward interior bay of a fuselage of an aircraft with each of the
side portions of the frame structure proximate a corresponding one of the airframe members;

at least one pair of mounting pins, each of the mounting pins disposed on and axially aligned with a respective one of the
opposing side portions of the frame structure and configured to project outwardly from each respective one of the opposing
side portions to align with and detachably secure to the corresponding one of the airframe members when the frame structure
is in a mounted position; and

a connector assembly configured to connect to avionics equipment on the frame structure, the connector assembly disposed on
the frame structure and having a plurality of connectors, including an alternating current connector of the plurality of connectors
configured to connect to a 115-volt alternating current source, a direct current connector of the plurality of connectors
configured to connect to a 28-volt direct current source, and a data bus connector of the plurality of connectors configured
to connect to a data bus of the aircraft;

wherein the modular avionics platform is one of a number of modular avionics platforms, each of the modular avionics platforms
mountable within and non-destructively releasably removable from the forward interior bay of the fuselage, with each of the
modular avionics platforms being configured to support one or more of the avionics equipment having different dimensions,
and to thereby enable modular installation of selected ones of the avionics equipment into the aircraft to perform a variety
of equipment-dependent missions.

US Pat. No. 9,291,434

METHOD AND SYSTEM FOR ELECTRONICALLY SHAPING DETONATED CHARGES

THE BOEING COMPANY, Chic...

1. A method of controlling the shape and direction of an explosion, the method comprising:
embedding a plurality of detonators in an explosive, and arranging the detonators in the explosive to produce a shaped explosion
of the explosive in a pre-set direction and having a pre-set intensity when triggered in a selected sequence;

sensing a direction of an incoming threat relative to a protected region, calculating an intercept vector for the incoming
threat, and sending a signal in response thereto by a sensor;

receiving information from the sensor pertaining to the intercept vector and determining a sequential firing pattern for the
detonators in response to the information from the sensor by a firing sequence calculator connected to trigger the detonators;
and

activating the firing sequence calculator to trigger the detonators in the sequential firing pattern to generate a counteracting
force substantially along the intercept vector.

US Pat. No. 9,609,756

PRINTED CIRCUIT BOARD ASSEMBLY METHODS

THE BOEING COMPANY, Chic...

1. A method comprising:
aligning a first portion of a magnetic core with respect to a first side of a printed circuit board (PCB) using a first alignment
device;

applying a first bonding material to a surface of at least one of the first portion of the magnetic core and a second portion
of the magnetic core;

coupling a second alignment device that retains the second portion of the magnetic core to the first alignment device, wherein,
when the first alignment device and the second alignment device are coupled, the first portion and the second portion of the
magnetic core are retained in a specified assembly position, the specified assembly position including a gap between the first
portion and the second portion of the magnetic core;

adjusting the gap between the first portion and the second portion of the magnetic core by adjustment of the first alignment
device or the second alignment device; and

curing the first bonding material.

US Pat. No. 9,188,448

METHODS AND SYSTEMS FOR DETERMINING AN ANCHORING LOCATION OF A MARINE VESSEL

The Boeing Company, Chic...

1. A system for determining an anchoring location of a marine vessel, the system comprising:
an anchorage database configured to store anchorage locations;
a first computing device configured to capture location data of the marine vessel along a route of the marine vessel; and
a second computing device comprising:
a memory area;
a location component that determines location data of the marine vessel; and
a processor programmed to:
receive, from the first computing device, the location data of the marine vessel, wherein the location data identifies that
the marine vessel has maintained a location between a first location and a second location over a predefined period of time
and does not identify the anchoring location of the marine vessel;

determine, from the location data, that a distance between the first location and the second location is less than a maximum
threshold distance;

based on the determination that the marine vessel traveled a distance less than the maximum threshold distance over a predefined
period of time, determine that the marine vessel is anchored; and

based on the determination that the marine vessel is anchored, identify an area between the first location and the second
location as the anchoring location, wherein the anchoring location is a location not identified as one of one or more anchoring
locations within the anchoring database or by the second computing device prior to determining that the marine vessel is anchored.

US Pat. No. 9,289,511

BIOCONJUGATED NANOPARTICLES

The Boeing Company, Chic...

1. A method comprising the steps of:
administering an effective amount of electromagnetic radiation to a biocompatible quantum dot conjugated to a targeting moiety
specific for a predictive marker of a target cell or a pathogenic organism;

wherein said electromagnetic radiation is soft x-rays from an external device having a wavelength in the range of 0.1 nm to
100 nm that interacts with the quantum dot thereby emitting light at an ultraviolet wavelength; and

inducing DNA damage or cellular membrane disruption to the target cell or the pathogenic organism from the emitted light at
the ultraviolet wavelength.

US Pat. No. 9,267,480

ELECTRICAL POWER GENERATING ENGINE FLYWHEEL WITH ACTIVE TORQUE CONTROL

THE BOEING COMPANY, Chic...

1. An apparatus, comprising:
a torque control for a crankshaft of an engine, the torque control comprising:
an electrical power control integrated with an engine control;
the crankshaft directly connected to:
a mechanical power take-off that extends externally from a side of a housing for a flywheel generator, the side being opposite
a side of the housing mounted to the engine; and

a rotating component of a flywheel, the flywheel directly attached to the crankshaft such that an axis of rotation of the
flywheel is aligned with an axis of rotation of the crankshaft;

a rotor directly connected to:
the flywheel; and
a cooling structure, such that an axis of rotation of the rotor is aligned with the axis of rotation of the flywheel, and
the rotor, the flywheel, and the cooling structure rotate together; and

a stator positioned with respect to the rotor such that the rotor and the stator together form an electric generator that
provides, when a rotation of the crankshaft rotates the rotor, an alternating current to an electrical power take-off connected
to a power converter connected to an electrical power bus, such that the electrical power bus comprises a connector to an
electrical power source distinct from the electrical power take-off.

US Pat. No. 9,395,041

SMALL FRAME CRAWLER SYSTEM

THE BOEING COMPANY, Chic...

1. An apparatus, comprising:
a robotic crawler capable of moving along an elongate frame on a structure to perform an operation, the robotic crawler comprising:
a guide configured to be situated on a side of the elongate frame having a wheel assembly comprising a wheel and a sphere;
wherein the sphere is situated within the wheel, the sphere being configured to contact and move along the side of the elongate
frame, and the wheel being configured to contact and move along a surface of the elongate frame;

a movement system configured to move the robotic crawler to a location along the elongate frame; and
a system configured to perform the operation on the structure at the location.

US Pat. No. 9,287,726

VIRTUAL CELL FOR BATTERY THERMAL MANAGEMENT

THE BOEING COMPANY, Chic...

1. A method for thermal battery management, the method comprising:
sensing, with at least one temperature sensor, a temperature of at least one battery cell in a battery pack;
sensing, with at least one current sensor, at least one current within the battery pack;
determining if the temperature of any of the battery cells in the battery pack exceeds a temperature limit (TLimit); and

activating at least one virtual cell to provide current or sink current for at least one of the battery cells in the battery
pack that exceeds the temperature limit,

wherein the battery cells are arranged in layers in the battery pack, and
wherein the battery cells, in each layer, are connected in parallel.

US Pat. No. 9,297,494

DAGGER PIN INTERFACE APPARATUS WITH SWIVEL PIN

The Boeing Company, Chic...

1. An apparatus for mounting a removable device to a structure, the apparatus comprising:
a first pin that is attachable to the structure where the first pin is stationary relative to the structure, the first pin
having a distal end surface that is configured for engaging in a first hole in a surface of the device;

a second pin that is attachable to the structure for pivoting movement of the second pin about a pivot axis relative to the
structure, the second pin having a distal end surface that is configured, for engaging in a second hole in the surface of
the device and causing the second pin to pivot about the pivot axis as the first and second pin distal end surfaces are engaged
in the respective first and second holes in the surface of the device;

the first pin having a center axis that passes through the first pin distal end surface;
the second pin having a center axis that passes through the second pin distal end surface; and,
a biasing device acting on the second pin, the biasing device urging the second pin to pivot about the pivot axis to a neutral
position of the second pin relative to the first pin where the first pin center axis and the second pin center axis are substantially
parallel.

US Pat. No. 9,047,771

SYSTEMS AND METHODS FOR GROUND COLLISION AVOIDANCE

The Boeing Company, Chic...

1. A system for aiding ground maneuvering of an airplane, said system comprising:
a first video camera mounted to an airplane for generating a first stream of video images that include a changing video scene
and a fixed image of a first extremity of said airplane;

a video display unit on the flight deck of said airplane capable of displaying video images; and
a computer system programmed to cause said video display unit to display a video image of said first stream in a first window
with a first graphical cue superimposed on said video image of said first stream, said first graphical cue representing projected
locations of said first extremity over ground during movement of said airplane.

US Pat. No. 9,276,391

FAULT-TOLERANT SELF-INDICATING SURGE PROTECTION SYSTEM FOR AIRCRAFT

The Boeing Company, Chic...

1. A fault-tolerant self-indicating surge protector system, the system comprising:
at least one surge protection module configured to couple to a power line and a surge grounding line to direct an unwanted
surge of electrical energy induced by a lightning strike away from a sensitive electrical or electronic component in an aircraft
to protect the aircraft from the lighting strike, comprising:

a first varistor module configured to couple to the power line and a middle node, and comprising a first varistor configured
to:

provide a first high impedance between the power line and the middle node if a first varistor voltage from the power line
to the middle node is below a first voltage threshold, wherein the first voltage threshold is greater than a peak voltage
level of the power line; and

absorb a surge current from the power line if the first varistor voltage is above the first voltage threshold; and
a second varistor module configured to couple to the middle node and the surge grounding line, and comprising a second varistor
configured to:

provide a second high impedance between the middle node and the surge grounding line if a second varistor voltage from the
middle node to the surge grounding line is below a second voltage threshold; and

absorb the surge current from the power line if the second varistor voltage is above the second voltage threshold; and
a fault detection circuit configured to indicate a fault in the at least one surge protection module based on a tap voltage
on the middle node.

US Pat. No. 9,114,886

METHOD AND SYSTEM FOR REDUCING THE FLAMMABILITY OF FUEL-TANKS ONBOARD AN AIRCRAFT

THE BOEING COMPANY, Chic...

16. A fuel vapor removal system onboard an aircraft, comprising:
a fuel tank having ullage containing an ullage mixture including fuel vapor and air;
a pumping device, configured to pump the ullage mixture in a pumping direction in a closed loop from the fuel tank ullage
and back;

an adsorption system, interposed in the closed loop, including an adsorber having adsorption media capable of adsorbing fuel
vapor from the ullage mixture; and

a controller, including a microprocessor and system memory, programmed to activate the pumping device, to pump the ullage
mixture from the ullage, through the adsorption system, and return a reduced fuel-air ratio ullage mixture back to the ullage.

US Pat. No. 9,278,758

SELF-CONFIGURING CABIN MANAGEMENT SYSTEM

The Boeing Company, Chic...

1. A passenger cabin system comprising:
a plurality of passenger control units through which passenger input can be received,
a plurality of passenger service units, each configured to perform a function based on an input command received from one
of the plurality of passenger control units,

one or more computer processors; and
a programming code, stored on a non-transitory computer readable medium, that when executed by operation of the one or more
computer processors, enables the passenger control units, the passenger service units, or a cabin management unit to on their
own, create a dynamic database dynamically linking at least one of the passenger control units to a separate one of the passenger
service units without the assistance of an in-flight entertainment system or an external passenger flight information system,
comprising:

determining how many control units of the plurality of passenger control units are disposed within a zone of the passenger
cabin system;

determining how many service units of the plurality of passenger service units are disposed within the zone of the passenger
cabin system; and

creating a database linking each control unit within the zone of the passenger cabin system to a corresponding service unit
within the zone, facilitating direct communication between each of the plurality of passenger control units and the linked
passenger service unit.

US Pat. No. 9,456,507

ECOLOGICAL METHOD FOR CONSTRUCTING CIRCUIT BOARDS

The Boeing Company, Chic...

1. A method for fabrication of a circuit board comprising:
preparing a Computer Aided Design (CAD) model of a multilayer circuit board with conductive elements defined by layer for
a plurality of layers;

introducing a first granular conductive material layer into a mold;
traversing a laser sintering head across the mold to sinter selected portions of the first granular conductive material layer
forming first layer conductive elements as defined by the CAD model for a first layer in the plurality of layers;

introducing an additional granular conductive material layer into the mold over the sintered selected portions of the first
layer and un-sintered portions of the first layer;

traversing the laser sintering head across the mold to sinter selected portions of the additional granular conductive material
layer forming additional layer conductive elements as defined by the CAD model for an additional layer in the plurality of
layers, the traversing speed and laser sintering power controlled to avoid fusing of un-sintered material in the first layer;

removing un-sintered granular conductive material from the sintered first conductive elements and additional conductive layer
elements, wherein the step of removing un-sintered granual conductive material comprises pneumatic purging;

infusing a dielectric material into a structure formed by the sintered first conductive elements and additional conductive
layer elements to fill space from which the un-sintered granular conductive material was removed.

US Pat. No. 9,278,448

POSITION CONTROL FOR A POSITIONING SYSTEM COMPRISING LARGER SCALE AND SMALLER SCALE POSITIONING MECHANISMS

THE BOEING COMPANY, Chic...

1. An apparatus, comprising:
a smaller scale positioning mechanism configured to move a tool within a smaller scale work space;
a larger scale positioning mechanism configured to change a position of the smaller scale work space within a larger scale
work space; and

a positioning system controller configured to receive a position command identifying a commanded position for the tool within
the larger scale work space, determine an error component using a difference between the commanded position and a current
position of the tool in the larger scale work space, determine a restoring component configured to move the tool toward a
selected position in the smaller scale work space, determine an acceleration for the smaller scale positioning mechanism and
an acceleration for the larger scale positioning mechanism using the error component, the restoring component, and an estimated
acceleration for the commanded position, and generate control signals for controlling the smaller scale positioning mechanism
and the larger scale positioning mechanism together to move the tool from the current position to the commanded position using
the error component and the restoring component.

US Pat. No. 9,276,774

VISUALIZING AND MODIFYING AD-HOC NETWORK NODES

The Boeing Company, Chic...

1. A method of managing a network the method comprising:
displaying, in a pictorial display updated and essentially in real-time, a plurality of live and virtual nodes of a physical
network and current geographic locations of each of the nodes, each node having one or more application capabilities registered
in a management system for the physical network, and further comprising:

determining a line of sight exists between a first live node and a first virtual node of the plurality of live and virtual
nodes, based on a simulated current geographic position of the first virtual node and a current geographic position of the
first live node; and

displaying a potential link along the determined line of sight between the two nodes that is updated essentially in real-time;
shadowing a first live node with a first virtual shadow node;
based on user input, modifying, on the display and on said first virtual shadow node via the physical network, one or more
application capabilities, wherein the one or more application capabilities meet at least one mission requirement;

providing a graphical depiction of network health data of the physical network within the pictorial display, wherein network
connections between nodes of the plurality of live and virtual nodes are shown as having one of a plurality of network performance
levels within the pictorial display using a respective distinctive visual style; and

based on user input, modifying, on the display and on said first live node via the physical network, the one or more application
capabilities, wherein the one or more application capabilities meet at least one mission requirement;

the method performed by the management system.

US Pat. No. 9,273,716

SELF-INDEXING NUT PLATE

The Boeing Company, Chic...

1. An aircraft comprising:
a plurality of spanner bars, each spanner bar having a pattern of mounting holes separated by lands; and
a plurality of nut plates engaging the spanner bars, each nut plate including:
a body;
a mounting surface affixed to the body, the mounting surface being disposed against at least one of the spanner bars; and
a first mounting post extending from the mounting surface and having a first undercut portion that abuts one of the lands;
a second mounting post extending from the mounting surface and having a second undercut portion that abuts one of the lands;
and

a generally L-shaped spring lever comprising a first end cantilevered from the body; a second, free end; a retractable locking
member extending generally downwardly from the free end of the spring lever and movable through a gap between a locked position
and an unlocked position; and a release grip ledge adjacent to and extending generally transversely with respect to the locking
member,

wherein the first and second mounting posts are configured to extend into corresponding mounting holes in at least one of
the plurality of spanner bars; and

wherein the locking member is configured to occupy at least a portion of the same hole as the second mounting post to prevent
the nut plate from disengaging at least one of the spanner bar bars when the spring lever is in a locked position.

US Pat. No. 9,170,125

PRESENTING WEATHER INFORMATION ON A DISPLAY

THE BOEING COMPANY, Chic...

1. A method for presenting weather information, the method comprising:
identifying a plurality of weather conditions present for a geographic region from weather data for the geographic region;
selecting a first geometry comprising a first spatial extension, wherein the first geometry is for a first weather condition
within the plurality of weather conditions, wherein the first geometry is based on a first type of the first weather condition,
and wherein the first geometry has a first level of transparency within the first spatial extension;

selecting a first color for the first geometry based on a severity of the first weather condition, wherein the color selected
is for a first border of the first geometry;

selecting a second geometry comprising a second spatial extension, wherein the second geometry is for a second weather condition
within the plurality of weather conditions, wherein the second geometry is based on a second type of the second weather condition,
wherein the second geometry has a second level of transparency within the second spatial extension, and wherein the first
spatial extension and the second spatial extension overlap at least in part; and

displaying the first geometry and the second geometry on a map of the geographic region.

US Pat. No. 9,262,641

SYSTEM AND METHODS OF PROVIDING DATA TO A MOBILE COMPUTING DEVICE

The Boeing Company, Chic...

1. A system for authorizing data to be provided to a mobile computing device, said system comprising a server computer that
comprises a processor and a memory coupled to said processor, said memory including processor-executable instructions for
performing the steps of: storing, in said memory, parameters for authorizing data to be provided to the mobile computing device;
determining at least one contextual cue associated with at least one of a task to be performed, the mobile computing device,
and a user of the mobile computing device, wherein the at least one contextual cue is associated with the parameters; authorizing
data to be provided to the mobile computing device when the at least one contextual cue aligns with the parameters; and providing
the data to the mobile computing device; wherein said memory further includes process-executable instructions for performing
the steps of determining a change in the at least one contextual cue; and one of denying and revoking the authorization when
the at least one contextual cue does not align with the parameters.

US Pat. No. 9,281,736

VIRTUAL ELLIPSE MOTOR

The Boeing Company, Chic...

1. A virtual ellipse electric motor comprising:
a fulcrum operable to bear a rotating radial dynamic load;
a wobble plate rotationally coupled to the fulcrum and operable to nutate around the fulcrum, and comprising an inner pericyclic
gear and an outer pericyclic gear;

a stationary gear operable to mesh with the outer pericyclic gear and provide leverage to the wobble plate;
a rotational output plate operable to mesh with the inner pericyclic gear and rotate in response to nutation of the wobble
plate; and

a stator comprising at least one electromagnet and operable to electromagnetically attract a first side of the wobble plate
such that a second side of the wobble plate is leveraged against the stationary gear and the rotational output plate.

US Pat. No. 9,872,384

ELONGATED, ULTRA HIGH CONDUCTIVITY ELECTRICAL CONDUCTORS FOR ELECTRONIC COMPONENTS AND VEHICLES, AND METHODS FOR PRODUCING THE SAME

The Boeing Company, Chic...

1. An elongated electrical conductor, comprising:
a conductor body defining a longitudinal axis, wherein the conductor body includes:
(i) an isotropically conductive matrix material; and
(ii) a plurality of anisotropically conductive particles interspersed within the isotropically conductive matrix material,
wherein each anisotropically conductive particle in the plurality of anisotropically conductive particles defines a respective
axis of enhanced electrical conductivity, and further wherein the respective axis of enhanced electrical conductivity of each
of the plurality of anisotropically conductive particles is at least substantially aligned with the longitudinal axis of the
conductor body.

US Pat. No. 9,321,090

FORMING TOOLS HAVING TEXTURED SURFACES

FORD GLOBAL TECHNOLOGIES,...

1. A method of manufacturing metal-formed components having a desired shape, comprising the steps of:
contouring a surface of a forming tool for forming a metal blank into the desired shape, wherein respective portions of the
metal blank flow over the contoured surface during forming;

identifying an intrinsic material flow pattern imparted to the metal blank according to a uniform coefficient of resistance
for the contoured surface;

comparing the intrinsic material flow pattern to a desired flow in order to identify regions of the contoured surface having
an insufficient flow that creates areas in the formed metal blank receiving less than a desired amount of metal; and

applying a surface microtexture onto the contoured surface in a pattern selected to alter metal flow along the identified
regions by providing a reduced coefficient of friction in the identified regions relative to a coefficient of friction of
adjacent regions of the contoured surface;

wherein the step of applying a surface microtexture onto the contoured surface is comprised of laser etching of microscopic
dimples according to the pattern, wherein the dimples are formed as raised features above the contoured surface, and wherein
each dimple is in a range of about 5-10 ?m in length and about 3 ?m in height.

US Pat. No. 9,289,949

OPTIMIZED CROSS-PLY ORIENTATION IN COMPOSITE LAMINATES

THE BOEING COMPANY, Chic...

1. A composite laminate aircraft wing skin having an axis of loading in-plane with the aircraft wing skin, the composite laminate
aircraft skin comprising:
a plurality of resin plies in the aircraft wing skin reinforced with unidirectional fibers, wherein the plurality of resin
plies comprises:

a first set of plies having a substantially straight first fiber orientation of substantially 0 degrees relative to the axis
of loading, the first set of plies extending a length of the wing, wherein the axis of loading substantially bisects the wing;
and

at least one first set of cross-plies having a second fiber orientation of ±? degrees relative to the axis of loading and
the first fiber orientation, wherein 0 is determined while the composite laminate aircraft wing skin is in a static position,
where ? is greater than or equal to approximately 25 degrees and less than or equal to approximately 43 degrees.

US Pat. No. 9,284,726

PYRAMID WAFFLE CORE STRUCTURE AND METHOD OF FABRICATION

The Boeing Company, Chic...

1. A structural core comprising:
a single layer of adjacent hollow pyramid-like structures, wherein the single layer is comprised of at least two rows of the
adjacent hollow pyramid-like structures, each pyramid-like structure formed from four faces having substantially straight
edges and having an open base, each open base in one of the at least two rows offset with respect to each open base in an
adjacent another of the at least two rows, the edges of each adjacent pyramid-like structure combining to form a truss-like
structure for providing support against transverse loads applied to the structural core.

US Pat. No. 9,274,089

APPARATUS AND A METHOD FOR MEASURING IN-PLANE ELASTIC CONSTANTS FOR A LAMINATE

The Boeing Company, Chic...

7. A method comprising:
simultaneously generating, by an acoustic wave generator, a plurality of acoustic waves that propagate through a laminate
along a plurality of in-plane directions;

detecting, by a plurality of acoustic transducers, acoustic waves propagating through the laminate, the acoustic transducers
being spaced apart from one another and positioned at one or more known distances from the acoustic wave generator along respective
in-plane directions, the acoustic transducers being configured to detect acoustic waves propagating through the laminate along
the respective in-plane directions; and

simultaneously calculating a plurality of elastic constants of the laminate as a function of velocities of the acoustic waves
detected by the acoustic transducers, the velocities being calculated as a function of the one or more known distances and
arrival times of the acoustic waves at the acoustic transducers.

US Pat. No. 9,187,818

HARDENED TITANIUM STRUCTURE FOR TRANSMISSION GEAR APPLICATIONS

THE BOEING COMPANY, Chic...

1. A method for manufacturing a spur gear comprising a cylindrical portion and teeth radially extending from the cylindrical
portion, the cylindrical portion and the teeth both comprising a metal alloy; the method comprising:
positioning the spur gear in a chamber;
generating an electromagnetic field that heats the spur gear;
injecting an inert gas from the chamber onto only the teeth and dedendum circle of the spur gear to cool the teeth of the
spur gear, but wherein the cylindrical portion of the spur gear within a root diameter of the spur gear is allowed to heat
via induction heating created by the electromagnetic field, the electromagnetic field and cooling selected so as to establish
an inverse thermal gradient through the cylindrical portion of the spur gear; and

maintaining the inverse thermal gradient between the cylindrical portion and the teeth until the spur gear reaches a desired
heat treatment.

US Pat. No. 9,295,032

SECURE AIRCRAFT DATA TRANSMISSION USING MULTIPLE COMMUNICATION CHANNELS

The Boeing Company, Chic...

1. A method for terrestrial data transmission between an aircraft and an external network, the method comprising:
identifying two or more communication channels available for terrestrial data transmission between the aircraft and the external
network; and

allocating data domains to be transmitted between the aircraft and the external network to each of the two or more communication
channels based on a channel security level of each of the two or more communication channels,

wherein at least two of the two or more communication channels are allocated to transmit the same data domain of the data
domains; and

generating instructions for reconstructing the same data domain after the same data domain is transmitted using the at least
two of the two or more communication channels.

US Pat. No. 9,278,826

SYSTEM AND METHOD FOR PRODUCING A THREE-DIMENSIONAL DRY FIBER PREFORM

The Boeing Company, Chic...

1. A preform forming machine for producing a three-dimensional dry fiber preform, comprising:
a forming block assembly having a forming table and a forming block and being positionable in a series of forming block assemblies;
a clamping plate assembly having a clamping table and a clamping plate and being positionable in a series of clamping plate
assemblies arranged in opposing relation to the series of forming block assemblies;

the forming block being configured to fold a ply stack over onto itself to form a web of the preform; and
the clamping plate being configured to clamp the ply stack to the forming table prior to and during the folding of the ply
stack.

US Pat. No. 9,176,226

RADAR TOMOGRAPHY USING DOPPLER-BASED PROJECTIONS

The Boeing Company, Chic...

1. A method for generating an image, comprising:
translating a radar system about a target area at a selected angular rate and at a predetermined radius from the target area;
transmitting a plurality of radar signals in a predetermined frequency range from the radar system as the radar system is
translated about the target area;

collecting a plurality of backscattered radar signals from the target area resulting from the plurality of transmitted radar
signals;

forming a plurality of Doppler-based projections from the plurality of backscattered radar signals; and
generating an image of the target area using radar tomography and the Doppler-based projections.

US Pat. No. 9,413,470

ELECTRONIC QUANTUM INFORMATION PROBABILITY TRANSFER

The Boeing Company, Chic...

1. A method of digitally communicating between a sending device and a receiving device, wherein each of the sending device
and the receiving device includes an entanglement set of entanglement pairs of qubits, wherein each qubit of the sending device
is entangled with a corresponding qubit of the receiving device, the method comprising:
sending a classical bit from the sending device to the receiving device by one of
(a) entangling each entanglement pair of the entanglement set of the sending device to produce a correlated distribution in
the entanglement set of the sending device in which every entanglement pair of the entanglement set of the receiving device
is entangled, or

(b) entangling less than all of the entanglement pairs of the entanglement set of the sending device to produce an uncorrelated
distribution in the entanglement set of the receiving device in which less than all entanglement pairs of the entanglement
set of the receiving device are entangled; and

receiving the classical bit at the receiving device from the sending device by one of
(a) determining that each entanglement pair of the entanglement set of the receiving device is in a possible entangled state
to identify the correlated distribution in the entanglement set of the receiving device, or

(b) determining that at least one of the entanglement pairs of the entanglement set of the receiving device is in a separable
state to identify the uncorrelated distribution in the entanglement set of the receiving device;

wherein the classical bit has one of two binary values that correspond to the correlated distribution and the uncorrelated
distribution.

US Pat. No. 9,294,599

PORTABLE COMMUNICATION DEVICES WITH ACCESSORY FUNCTIONS AND RELATED METHODS

The Boeing Company, Chic...

1. A portable communication device for use in supporting voice and/or data communication, said portable communication device
comprising:
a housing;
a processor disposed at least partially within said housing;
an interface connector disposed at said housing and coupled to said processor; and
a back panel, wherein said housing is configured such that said back panel is removably coupleable to said housing and such
that a module is coupleable to said portable communication device in place of said back panel when said back panel is uncoupled
from said housing, said module is communicatively coupleable to said interface connector when said module is coupled to said
portable communication device, and said module is configured to provide at least one accessory function.

US Pat. No. 9,495,877

AIRSPACE DECONFLICTION SYSTEM AND METHOD

The Boeing Company, Chic...

1. An aircraft deconfliction system comprising:
a registration system comprising an airspace database;
a registered airspace, wherein registration details of said registered airspace are logged in said airspace database; and
an aircraft assigned to said registered airspace, said aircraft comprising:
a flight control system;
a guidance computer controlling said flight control system based on a pilot input; and
an override unit in communication with said guidance computer, wherein said override unit overrides said pilot input when
said aircraft breaches said registered airspace.

US Pat. No. 9,086,085

REMOVEABLE FASTENER RECESS INSERT AND METHOD FOR MAKING SAME

The Boeing Company, Chic...

1. A fastening system comprising:
an aircraft fastener having a head portion and a shaft portion extending therefrom, the head portion having a driver recess
formed therein, the recess having a recess shape and a recess depth; and

a pre-made insert consisting of a substantially elastic body having the same shape and depth as the recess prior to being
seated in the recess, the insert completely filling the recess of the head portion such that an interference fit forms between
the insert and the recess when the insert is seated within the recess.

US Pat. No. 9,045,218

AUTONOMOUS AIRCRAFT WITH DISCONNECTABLE TETHER

The Boeing Company, Chic...

1. A system, comprising:
an aircraft including a control system configured to control movement of the aircraft;
a tether configured to couple the aircraft to a remote power supply, wherein the remote power supply provides power to the
aircraft via the tether, and wherein the aircraft is configured to disconnect from the tether in response to a command signal
from the control system; and

a release mechanism coupled to the aircraft, the release mechanism configured to release the tether in response to the command
signal, wherein the release mechanism includes tether hooks configured to receive a tether ball coupled to the tether, wherein
the tether hooks are configured to hold the tether ball when in a first configuration, and wherein the tether hooks are configured
to release the tether ball when in a second configuration.

US Pat. No. 9,455,461

SYSTEM AND METHOD FOR FUEL CELL DEGRADATION MANAGEMENT

THE BOEING COMPANY, Chic...

1. A fuel cell system, comprising:
a first power source comprising a fuel cell assembly electrically connected to a load;
a second power source electrically connected to the load; and
a fuel cell discharge controller communicatively coupled to the first power source and the second power source and programmed
to receive a degradation input from either the first power source or the second power source and transmit a control signal
based on the degradation input, wherein the control signal alternates operation between the first power source and the second
power source to switch the power provided to the load between one of the first power source and the second power source based
on the degradation input to reduce a degradation of the first power source.

US Pat. No. 9,313,773

AIRCRAFT COMMUNICATIONS SWITCHING SYSTEM

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a plurality of wireless communications units on an aircraft, the wireless communications units being configured to be connected
to a communication interface via a wired bus;

an avionics system on the aircraft, the avionics system being configured to be connected to an avionics interface, the avionics
system comprising a user interface, wherein the user interface comprises:

a source field configured to select a source of communications for a communications operation;
a destination field configured to select a destination for the communications operation; and
a radio assignments field configured to display a wireless communications unit in the plurality of wireless communications
units that is available for the communications operation based on the selected source and destination; and

a communications manager configured to:
identify the plurality of wireless communications units connected to the communications interface;
receive the communications operation from the user interface in the avionics system via the avionics interface;
identify the wireless communications unit displayed in the radio assignments field in the plurality of communications units
connected to the communications interface; and

control operation of the wireless communications unit to perform the communications operation.

US Pat. No. 9,291,187

NUT, WASHER AND FASTENER HEAD FOR ELECTROMAGNETIC EFFECT PROTECTION

The Boeing Company, Chic...

1. A fastener system for composite structure providing electromagnetic energy protection comprising:
a fastener having a head with an engagement surface and a shank having a threaded end;
a nut received on the threaded end of the fastener, said nut having an engagement surface;wherein at least one of the head engagement surface and the nut engagement surface incorporates a reduced area portion engaging
a first mating surface or second mating surface, respectively, thereby creating a pressure contained system to prevent high
energy sparks (HPE) and edge sparking during lightning conditions.

US Pat. No. 9,293,033

WIRELESS FUEL SENSOR SYSTEM

THE BOEING COMPANY, Chic...

1. An aircraft fuel sensor system comprising:
a group of sensor units located in a fuel tank of an aircraft;
a wireless system configured to send a number of wireless power signals and a number of wireless data collection signals to
the group of sensor units under a control of a sensor controller and receive sensor data in a number of wireless response
signals sent from the group of sensor units;

the sensor controller, wherein the sensor controller is configured to cause the wireless system to send the number of wireless
power signals to the group of sensor units; cause the wireless system to send the number of wireless data collection signals
to the group of sensor units after the number of wireless power signals have been sent to the group of sensor units; and receive
the sensor data transmitted wirelessly in the number of wireless response signals from the wireless system; and

a radio frequency window formed in a structure of the fuel tank, wherein the radio frequency window facilitates the passage
at least one of the wireless response signals, the wireless power signals, or the wireless data collection signals through
the structure, and wherein the radio frequency window is formed of a physical aperture in the structure and a material placed
in the physical aperture, wherein the material facilitates the passage of at least one of the wireless response signals, the
wireless power signals, or the wireless data collection signals through the radio frequency window.

US Pat. No. 9,221,230

HONEYCOMB STRUCTURE

THE BOEING COMPANY, Chic...

1. A non-planar honeycomb structure comprising:
a first surface;
a second surface opposite the first surface;
at least one ribbon comprising side edges along which the at least one ribbon is folded, the side edges partially defining
sections of the at least one ribbon, wherein at least one of the side edges of the at least one ribbon is not substantially
parallel to another one of the side edges of the at least one ribbon, the sections comprising:

first section edges forming at least a portion of the first surface of the non-planar honeycomb structure, wherein the first
section edges of at least two adjacent sections are not collinear when the at least one ribbon is unfolded flat; and

second section edges forming at least a portion of the second surface of the non-planar honeycomb structure, wherein the second
section edges of the at least two adjacent sections are not collinear when the at least one ribbon is unfolded flat; and

cells formed by folding the at least one ribbon along the side edges.

US Pat. No. 9,565,749

CIRCUIT OBFUSCATION USING DIFFERING DIELECTRIC CONSTANTS

THE BOEING COMPANY, Chic...

1. A method of manufacturing an obfuscated radio frequency circuit comprising:
forming a dielectric layer comprising an overall length dimension perpendicular to an overall width dimension, wherein the
dielectric layer comprises a plurality of dielectric substrates having differing dielectric constants in order to achieve
a required function of the radio frequency circuit while obfuscating the required function of the radio frequency circuit,
wherein each of the plurality of dielectric substrates is disposed adjacent to one another along only one of the length dimension
and the width dimension; and

forming a metallization layer disposed on the dielectric layer.

US Pat. No. 9,261,444

APPARATUS, SYSTEM, AND METHOD FOR IN SITU STRENGTH TESTING OF A BONDED JOINT

The Boeing Company, Chic...

1. A system for testing the strength of a bonded joint between two components, the bonded joint comprising an adhesive interposed
between the two components, the system comprising:
at least one element force energizer that creates an actual mechanical stress in the bonded joint when actuated, wherein the
at least one element force energizer is embedded in at least one of the two components;

an energy interface that is connectable to a power source, the energy interface being in electrical communication with the
at least one element force energizer; and

a sensor that detects the actual mechanical stress in the bonded joint.

US Pat. No. 9,083,169

SELF-INDEXING NUT PLATE

The Boeing Company, Chic...

1. An aircraft having a primary support structure, the aircraft comprising:
a secondary support structure; and
a nut plate engaging the secondary support structure, the nut plate including:
a body having a mounting surface against the secondary support structure and defining an internally threaded bore;
at least one locator protrusion engaging a mounting hole in the secondary support structure to constrain motion of the nut
plate along the secondary support structure in a first direction; and

a locking member occupying a space between one of the first and second posts and a land, the locking member including a first
end cantilevered to the body, a second, free end, and a release grip connected to the free end and extending outwardly from
the locking member, the member being operable to constrain motion of the nut plate in a second direction, the second direction
differing from the first direction,

wherein the at least one locator protrusion includes first and second posts, the posts extending from the mounting surface
and through respective holes in the secondary support structure and including an undercut portion in each of the first and
second post, the undercut portions being operable to constrain motion of the nut plate in a third direction.

US Pat. No. 9,455,486

INTEGRATED CIRCULATOR FOR PHASED ARRAYS

The Boeing Company, Chic...

1. An apparatus, comprising:
a first magnetic substrate having a first surface opposite a second surface, wherein a first ground plane is formed on the
first surface, wherein the first magnetic substrate is not electrically coupled to any radiofrequency (RF) trace via the first
surface, wherein the first magnetic substrate is not electrically coupled to any RF trace via the second surface, and wherein
each of the first surface and the second surface has a hexagonal shape;

a dielectric layer comprising a multi-port junction circuit disposed on a first side of the dielectric layer, wherein the
multi-port junction circuit is dimensioned to be resonant within a first frequency range, wherein the first side faces the
second surface, wherein the multi-port junction circuit is coupled to a plurality of RF transmission traces, wherein a first
RF transmission trace of the plurality of RF transmission traces forms an input port, and wherein a second RF transmission
trace of the plurality of RF transmission traces forms an output port, and wherein each of the first side and a second side
of the dielectric layer has the hexagonal shape;

a second ground plane disposed on the second side of the dielectric layer; and
a first magnet proximate to the multi-port junction circuit of the dielectric layer, such that the first magnet is configured
to excite a unidirectional magnetic flux field in the first magnetic substrate that limits electromagnetic wave propagation
to a single direction in the multi-port junction circuit.

US Pat. No. 9,439,502

HANDHELD TOOL FOR APPLYING A FLUID ONTO A SURFACE

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a structure;
an applicator associated with the structure;
a first control device associated with the structure, wherein applying a first force to the first control device causes the
applicator to move relative to a center axis of the applicator;

an actuation device configured to create reciprocating motion in response to the first force being applied to the first control
device; and

a second control device associated with the structure, wherein applying a second force to the second control device causes
a fluid to be delivered from a fluid dispensing system to the applicator.

US Pat. No. 9,387,657

METHOD OF FABRICATING A CURVED COMPOSITE STRUCTURE USING COMPOSITE PREPREG TAPE

THE BOEING COMPANY, Chic...

1. A method of laying up a composite part on a tool, comprising:
providing a composite resin tape reinforced with unidirectional fibers having a substantially zero degree fiber orientation;
placing the composite resin tape on a deformable carrier film;
forming the composite resin tape and the carrier film onto a first curved surface on a forming tool;
forming the composite resin tape and the carrier film about a curved axis onto a second curved surface on the forming tool;
and

removing the carrier film from the composite resin tape;
wherein forming the composite resin tape and the carrier film includes deforming the composite resin tape and the carrier
film by stretching the carrier film, stretching comprising changing one of a length or a width of the carrier film.

US Pat. No. 9,238,334

COMPOSITE LAYER FORMING SYSTEM

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a platform configured to receive a tool;
a number of compressible supports configured to be placed on the platform in a number of locations such that a stack of composite
layers positioned on the tool and the number of compressible supports is substantially flat on the tool and the stack of composite
layers is substantially flat on the number of compressible supports; and

a flexible sheet configured to be placed on top of the stack of composite layers such that a vacuum drawn on the flexible
sheet results in the flexible sheet applying a vacuum load on the stack of composite layers on the tool and the number of
compressible supports such that the stack of composite layers forms a desired shape on the tool and the number of compressible
supports compress during forming of the desired shape.

US Pat. No. 9,188,644

LATENCY MEASUREMENT SYSTEM AND METHOD

The Boeing Company, Chic...

1. A latency measurement system, the system comprising:
an event generation device that generates an event used to measure system latency;
a component test system that receives the event and in response outputs a test component output signal and changes a state
of a zero-latency indicator to produce a visual output representing receipt of the event;

a receiving system that receives the test component output signal and outputs a corresponding visible element;
a camera that generates a series of recorded images, where each recorded image contains an image of the zero-latency indicator
and an image of the visible element; and

a processor that determines the system latency by determining a time difference in the series of recorded images between a
representation of an occurrence of the change of state of the zero-latency indicator in the image and a representation of
the occurrence of the event in the image of the visible element.

US Pat. No. 9,388,740

THERMOELECTRIC GENERATOR IN TURBINE ENGINE NOZZLES

The Boeing Company, Chic...

1. A core nozzle for a gas turbine engine, comprising:
a core nozzle wall defining a core, configured to receive a core stream of the gas turbine engine;
a cowling assembly coupled to the core nozzle wall, defining a fan flow region configured to receive a fan stream of the gas
turbine engine;

a thermoelectric generator assembly positioned in a plenum;
a first inlet of the plenum configured to transfer a portion of the core stream to the thermoelectric generator assembly;
a second inlet of the plenum configured to transfer a portion of the fan stream to the thermoelectric generator assembly;
and

an outlet of the plenum configured to combine and discharge the portion of the fan stream and the portion of the core stream
into the fan stream.

US Pat. No. 9,222,006

JOINING A THERMOPLASTIC MATERIAL AND A METAL

THE BOEING COMPANY, Chic...

1. A method comprising:
forming a sol-gel solution comprising:
aging zirconium n-propoxide in a solvent to form a first part for the sol-gel solution;
combining the first part with deionized water to form a second part for the sol-gel solution;
combining aminoaryltrialkoxysilane with an alcohol to form a third part for the sol-gel solution;
combining the third part with the second part to form a mixture for the sol-gel solution;
aging the mixture to form the sol-gel solution comprising a mole balance ratio of 1:5 between the zirconium n-propoxide and
the aminoaryltrialkoxysilane;

applying the sol-gel solution to a metal to form a surface treated metal; and
adhering a thermoplastic material to the surface treated metal.

US Pat. No. 9,174,381

ADJUSTABLE SEALANT DISPENSING SYSTEM

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a dispenser configured to receive a sealant material from a sealant source and dispense the sealant material through an output
of the dispenser; and

an adjustment system associated with the dispenser and configured to change a configuration of the output, wherein the adjustment
system comprises two moveable screws positioned at the output of the dispenser, wherein movement of the two moveable screws
changes the configuration of the output of the dispenser when the two moveable screws move in and out of the output of the
dispenser to restrict the output, the two moveable screws rotate about an axis that is substantially perpendicular to the
output of the dispenser, the output of the dispenser has a width that is restricted along the axis of the two moveable screws,
and movement of the two moveable screws along the axis changes an entirety of the width of the output.

US Pat. No. 9,391,373

INFLATABLE ANTENNA

The Boeing Company, Chic...

1. An inflatable structure, comprising:
an inflatable membrane for forming the structure;
a first radio frequency (RF) reflective portion integral to the inflatable membrane; and
a second RF reflective portion integral to the inflatable membrane;
a horn;
a mounting frame having a perimeter, the mounting frame being attached to the inflatable membrane at the first RF reflective
portion around the perimeter of the mounting frame and configured to be releasably secured to an opening of the horn;

a bracket attached to a back of the horn opposite the opening of the horn, the bracket being configured for releasably attaching
the inflatable structure to a base support;

wherein, when the membrane is inflated, the first RF reflective portion and the second RF reflective portion oppose each other
to form an antenna.

US Pat. No. 9,373,184

AUTOMATIC WINDOW PLACEMENT

The Boeing Company, Chic...

1. A method of rendering data on a display device, wherein the data represents a display area to be rendered, the method comprising:
receiving data representative of graphics objects rendered on the display device;
analyzing the data to identify white space areas;
comparing the white space areas to the display area to be rendered on the display device, wherein the white space areas are
areas free of displayed objects according to at least one criterion;

determining whether the display area to be rendered fits within a white space area;
determining whether the display area to be rendered can be reduced in size to fit within a white space area;
determining priorities for the rendered graphics objects, wherein determining priorities includes accessing data indicating
(1) whether each rendered graphics object can be obscured, and (2) the relative importance of the rendered graphics objects;
and

if the display area to be rendered does not fit within a white space area and cannot be reduced in size to fit within a white
space area, rendering the display area over a selected one of the rendered graphics objects, wherein the selected one of the
rendered graphics objects is based on the priorities.

US Pat. No. 9,294,321

BIT SIGNAL STRUCTURE FOR DIFFERENTIALLY ENCODED BROADCASTS

The Boeing Company, Chic...

1. A method comprising:
receiving, at a differential encoder, data for transmission while the differential encoder is in a first logical state; and
encoding a portion of the data using a transmission code to generate an encoded signal, wherein the transmission code is selected
from a set of code words, and wherein the transmission code is selected so that the differential encoder enters a second logical
state that is different than the first logical state after encoding the portion of the data; and

encoding a second portion of the data using a second transmission code to generate a second encoded signal, wherein the second
transmission code is selected from the set of code words, and wherein the second transmission code is selected so that the
differential encoder enters a third logical state that is different than the second logical state after encoding the second
portion of the data.

US Pat. No. 9,201,905

SEMANTICALLY MEDIATED ACCESS TO KNOWLEDGE

THE BOEING COMPANY, Chic...

1. A system for positioning data within a network, the system comprising:
a processor configured to execute a knowledge manager configured to receive a query from a querent, the knowledge manager
further configured to:

receive the query from the querent, and determine whether the query is in logical form, and responsive to a determination
that the query is in logical form, compare entries of the logical form query with canonical models passed from a semantic
query engine, and determine whether the entries of the logical form query match entries of the canonical models, and responsive
to a determination that the entries of the logical form query match the entries of the canonical models, pass a relational
form query to the knowledge manager;

determine whether the query is a session command, and responsive to a determination that the query is a session command, determine
whether the querent ends a session, and responsive to a determination that the querent ends the session, the knowledge manager
updates all caches, marks all waypoints, generates reports, and clears contexts; and

process the query across a number of resources to generate a result;
the processor further configured to execute a canonical model manager having a number of models used to identify relationships
between types of information within the number of resources and the query; and

the processor further configured to execute a context manager configured to manage the context of the query and the relationships
identified by the canonical model manager, to position the number of resources for access by the knowledge manager.

US Pat. No. 9,169,017

AIRCRAFT INTERIOR LIGHTING SYSTEM USING STRUCTURED MICRO LENS ARRAYS

THE BOEING COMPANY, Chic...

1. An illumination fixture for an aircraft comprising:
an illumination source, the illumination source having a plurality of LEDs in a plurality of colors;
a communication component coupled to the illumination source to generate variable color light emissions; and
an optical module attached to the illumination source for collection of light emissions from the illumination source and distribution
of the collected light emissions over a desired distribution profile, the optical module being adaptive to shape the variable
color light emissions to a desired pattern, wherein the optical module comprises:

a collimator lens attached to the illumination source to align the variable color light emissions from the illumination source
to form a collimated beam;

a structured micro lens array (SMLA) spatially separated from and in light communication with the collimator lens to distribute
the collimated beam over a desired distribution profile, the SMLA positioned approximately planer to the collimated beam exiting
the collimator lens; and

a reflective device spatially separated from and in light communication with the collimator lens, the reflective device redirecting
the collimated beam exiting the collimator lens towards the SMLA, the reflective device at a non-straight angle relative to
both the collimator lens and the SMLA.

US Pat. No. 9,150,700

WRINKLE REDUCTION IN UNCURED COMPOSITE LAMINATES

THE BOEING COMPANY, Chic...

1. A method of reducing a wrinkle in a fiber reinforced impregnated resin ply, comprising:
forming a layup comprising said ply, the layup defining a surface; and
subjecting the wrinkle to vibrations while applying downward pressure relative to the surface following forming said layup
and prior to compacting and curing said layup, said vibrations having a frequency of at least 15,000 Hz and an amplitude of
at least 0.0005 inches applied with a flat face head and the vibrations being normal to the surface.

US Pat. No. 9,105,790

DETECTOR FOR PLASTIC OPTICAL FIBER NETWORKS

THE BOEING COMPANY, Chic...

1. An optical detector comprising:
a substrate having a type of conductivity;
an intrinsic region above the substrate, the intrinsic region having a surface; and
a first metal layer on a portion of the surface of the intrinsic region, the first metal layer having a thickness from about
50 angstroms to about 100 angstroms, and the thickness being configured to allow a plurality of photons to pass through the
first metal layer into the intrinsic region and form a rectifying contact with the intrinsic region, and wherein the substrate,
the intrinsic region, and the first metal layer form a Schottky barrier diode.

US Pat. No. 9,082,209

METHOD AND APPARATUS FOR REWORKING INCONSISTENCIES ON PARTS

THE BOEING COMPANY, Chic...

1. A method for reworking an inconsistency on a part, the method comprising:
identifying image data for the inconsistency on the part using data for the part generated by a nondestructive evaluation
system;

identifying information about the inconsistency using the image data;
generating rework image data using the information identified about the inconsistency in which the rework image data comprises
a number of patch images;

projecting the number of patch images onto a rework material as a number of patch projections for use in forming a patch for
the inconsistency;

forming a number of patch layers from the rework material using the number of patch projections of the number of patch images
on the rework material; and

applying the number of patch layers over the inconsistency to form the patch for the inconsistency.

US Pat. No. 10,091,916

FABRICATION OF CERAMIC MATRIX COMPOSITES WITH CARBON NANOTUBES AND GRAPHENE

The Boeing Company, Chic...

1. A method for forming a ceramic matrix composite structure, the method comprising:providing a mixture of carbon nanotubes, graphene, and silicon carbon nitride;
heating the mixture to bond the carbon nanotubes and the graphene; and
sintering the silicon carbon nitride in the mixture.

US Pat. No. 9,355,566

SYSTEMS AND METHODS FOR CONTROLLING AIRCRAFT ARRIVALS AT A WAYPOINT

The Boeing Company, Chic...

1. A method of controlling aircraft arrivals at a merging waypoint, the method comprising:
defining a tie waypoint at a first distance from the merging waypoint;
generating a first parameter set of flight instructions for aircraft arriving at the tie waypoint, the first parameter set
including an aircraft speed instruction for a target separation between a first aircraft arriving at a target waypoint downstream
of the tie waypoint and a second aircraft arriving at the target waypoint;

defining a diversionary flight path at a second distance from the merging waypoint, wherein the second distance is less than
the first distance; and

generating a second parameter set of flight instructions for the first aircraft arriving at the diversionary flight path,
the second parameter set of flight instructions based on target aircraft capacity at the merging waypoint, the second parameter
set including instructions for the first aircraft to follow at least a part of the diversionary flight path before flying
to the merging waypoint, wherein a total flight path distance of the first aircraft is to increase when an expected arrival
of the first and second aircraft at the target waypoint has a separation that is less than a threshold separation.

US Pat. No. 9,352,509

TOOLS AND METHODS FOR USE IN REMOVING A COATING

The Boeing Company, Chic...

1. A tool for use in removing a coating from at least one of a surface and a fastener head recessed within the surface and
having an outer face that is generally flush with the surface, the tool comprising:
a first scraper configured to abrasively engage the coating on at least one of the surface and the outer face of the fastener
head, wherein the first scraper is rotatable relative to the fastener head; and

a second scraper sized to abrasively engage the coating in a recess in the fastener head, wherein the second scraper is rotatable
within the recess; and

a spring configured to bias an abrasive end of the first scraper away from a trailing end of the second scraper and against
the at least one of the surface and the outer face of the fastener head as an abrasive end of the second scraper engages the
coating in the recess.

US Pat. No. 9,297,068

WEAR PARTS HAVING COATING RUN-OUT AND METHODS OF PRODUCING SAME

The Boeing Company, Chic...

1. A method of coating a wear part surface, the method comprising:
positioning a masking jig relative to a wear part within a chamber of a chemical vapor deposition machine, wherein the wear
part includes a wear part surface to be coated, wherein the positioning defines a volume between the masking jig and the wear
part surface, wherein the masking jig includes an overhang, wherein the positioning includes positioning the overhang in a
spaced-apart position relative to the wear part surface to be coated to define the volume between the masking jig and the
wear part surface, and wherein the positioning results in the masking jig not extending across an entirety of the wear part
and the masking jig not engaging the wear part surface; and

after the positioning, depositing a material to the wear part surface resulting in a deposited material, wherein the depositing
utilizes chemical vapor deposition including inducing an electric field in the chamber, wherein the position of the masking
jig relative to the wear part surface defines a region of reduced electric field within the volume between the masking jig
and the wear part surface during the inducing, and wherein the deposited material defines a coating profile in which a thickness
of the deposited material is not uniform across the wear part surface as a result of the masking jig being positioned relative
to the wear part;

wherein the wear part is constructed of at least one of steel, high-strength steel, stainless steel, aluminum, aluminum alloy,
titanium, titanium alloy, nickel, nickel alloy, molybdenum, and molybdenum alloy;

wherein the masking jig is constructed of a conductive material; and
wherein during the depositing, the wear part and the masking jig both serve as an electrode and have an equal potential.

US Pat. No. 9,227,718

LOWER JOINTS BETWEEN OUTBOARD WING BOXES AND CENTER WING SECTIONS OF AIRCRAFT WING ASSEMBLIES

The Boeing Company, Chic...

1. A wing assembly for an aircraft, the wing assembly comprising:
a left wing box;
a right wing box;
a wing center section;
a left lower joint assembly that defines a left lower joint with the left wing box and the wing center section; and
a right lower joint assembly that defines a right lower joint between the right wing box and the wing center section;
wherein the left wing box and the right wing box are constructed substantially of a first material having a first coefficient
of thermal expansion, wherein the wing center section is constructed substantially of a second material that is different
from the first material and that has a second coefficient of thermal expansion that is greater than the first coefficient
of thermal expansion, and wherein the left lower joint assembly and the right lower joint assembly are constructed substantially
of a third material that is different from the first material and the second material and that has a third coefficient of
thermal expansion that is greater than the first coefficient of thermal expansion and less than the second coefficient of
thermal expansion.

US Pat. No. 9,199,419

SYSTEM AND METHOD FOR FACILITATING FLUID MOVEMENT IN CLOSE-MOLDED COMPOSITE PARTS

The Boeing Company, Chic...

1. A method of forming a fluid flow channel in a vacuum bagging system, comprising the steps of:
mounting a strip of contact layer along a first portion of a part inner surface of a composite part formed of pre-impregnated
fiber-reinforced material and positionable within an outer mold line tool, the strip of contact layer extending from a part
interior of the composite part to at least one part end of the composite part and having a contact layer width defined by
opposing contact layer side edges, the strip of contact layer being located adjacent to and outside of a second portion of
the composite part such that an internal vacuum bag applies vacuum pressure directly onto the part inner surface of the second
portion not covered by the strip of contact layer;

mounting a strip of inner layer to the strip of contact layer, the strip of inner layer having an inner layer width that is
no greater than the contact layer width and being positioned between opposing contact layer side edges;

extending the contact layer to at least one part end of the composite part; and
positioning an internal vacuum bag on an interior of the part inner surface such that the internal vacuum bag is located on
a side of the inner layer opposite the contact layer, the internal vacuum bag covering an inner mold line tool having an inner
mold line tool width, the contact layer width of the strip of contact layer being less than the inner mold line tool width.

US Pat. No. 9,464,214

THERMALLY CONDUCTIVE FLEXIBLE ADHESIVE FOR AEROSPACE APPLICATIONS

The Boeing Company, Chic...

1. A method of forming a thermally conductive flexible bond for use in an electronic board, the method comprising:
providing one or more adhesive components, wherein the one or more adhesive components comprise boron nitride particles having
(3-glycidyloxypropyl) triethoxysilane attached to a surface of the boron nitride particles, and

wherein the one or more adhesive components comprise a urethane modified epoxy;
forming an adhesive material from the one or more adhesive components; applying the adhesive material onto a surface of the
electronic board; forming a contact between an electronic component and the adhesive material applied to the surface of the
electric board; and

curing the adhesive material thereby forming a cured adhesive structure between the electric board and the electronic component,
wherein the cured adhesive structure provides the thermally conductive flexible bond between the electric board and the electronic
component.

US Pat. No. 9,413,456

NON-LINEAR OPTICAL RECEIVER

THE BOEING COMPANY, Chic...

11. An apparatus comprising:
a receiver configured: to receive a plurality of optical signals having a plurality of different frequencies at the receiver;
to send the plurality of optical signals received at the receiver through a first non-linear optical element in the receiver
such that a first resulting optical signal is generated that has a first frequency based on a combination of the plurality
of different frequencies; to send the plurality of optical signals received at the receiver through a second non-linear optical
element in the receiver such that a second resulting optical signal is generated that has a second frequency based on a combination
of the plurality of different frequencies; to select one of the first resulting optical signal or the second resulting optical
signal as a selected optical signal, wherein the selected optical signal is different from at least one other optical signal
received at the receiver, the other optical signal comprising an optical signal selected from the group consisting of background
optical signals, intentional optical signals, and combinations thereof; and to identify information in the resulting optical
signal.

US Pat. No. 9,352,435

MAGNET SENSING HOLE DRILLER AND METHOD THEREFOR

The Boeing Company, Chic...

1. A portable device to drill holes comprising:
a platform;
a plurality of wheel sets coupled to the platform, the plurality of wheel sets engaging and moving the portable device along
a surface to be drilled;

a drive system for driving the plurality of wheels;
an attachment mechanism positioned on an underside of the platform for securing the device to the surface;
a control board for controlling operating of the device;
a drill assembly coupled to the platform;
a drill feed assembly coupled to the drill assembly for raising and lowering the drill spindle assembly;
a drive table for positioning the drill assembly in an XY plane;
a power supply for powering the device;
an antenna coupled to the control board for sending location information and receiving drill locations;
sensors for finding magnet locations identified by a magnet separate from the portable device; and
wherein the control board receives target signals and moves the portable device to a target drill location on the surface,
the control board adjusting an angle between the platform and the surface based on readings from the sensors.

US Pat. No. 9,352,514

FUSELAGE MANDREL INSERT AND METHOD

The Boeing Company, Chic...

1. A method of forming an elongated composite structure using a mandrel employing a pneumatic tool, the method comprising:
providing at least one flexible elongated pneumatic tool defining a generally vertical end having a generally tapered top
surface portion that terminates in a generally horizontal uppermost top surface;

providing at least one elongated insert having a first end defining a generally vertical surface portion and having a cantilevered
retainer extending therefrom, the insert being generally rigid;

inserting the elongated pneumatic tool into a mandrel cavity;
inserting the insert into the mandrel cavity such that the generally vertical surface portion of the first end of the insert
is adjacent the generally vertical end of the elongated pneumatic tool and the retainer extends over the end of the elongated
pneumatic tool to place the generally vertical surface portion of the first end of the insert in a close or abutting relationship
with the generally vertical end of the flexible elongated pneumatic tool; and

applying composite material to the mandrel, the pneumatic tool, and the retainer to the elongated composite structure.

US Pat. No. 9,316,506

METHOD AND APPARATUS FOR DISPLAYING VERTICAL TERRAIN INFORMATION

THE BOEING COMPANY, Chic...

1. A method for presenting on a display, terrain along a route of a vehicle, the route comprises a path of the vehicle, wherein
the path comprises a first segment independent of a current heading of the vehicle, the method comprising:
processing terrain data in a processor unit receiving a present location, of the vehicle, from a location device;
receiving in the processor unit, a selection of a distance for a width for each segment of the route;
displaying, on the display, a vertical profile side view of terrain within the width along the route, such that in response
to the present location of the vehicle being offset from a centerline of the first segment, laterally to one side of the centerline
of the first segment, the processor expands the width, only on the one side of the first segment, from the present location,
along a line of the offset, by one-half of the distance; and

displaying a number of graphical indicators, on the display, of a position of the terrain, relative to a left side of and
a right side of the vehicle, along the route.

US Pat. No. 9,293,820

COMPENSATING FOR A NON-IDEAL SURFACE OF A REFLECTOR IN A SATELLITE COMMUNICATION SYSTEM

The Boeing Company, Chic...

1. A system comprising:
a beamformer configured to measure amplitudes and phases of signals reflected off a reflector of a satellite, the amplitudes
and phases forming a first set of measurements; and

a computing apparatus configured to calculate an element correlation matrix as a function of the first set of measurements,
the element correlation matrix representing a radiated feed element pattern off the reflector,

wherein the beamformer is configured to generate a formed beam pattern adjusted based on the element correlation matrix.

US Pat. No. 9,260,197

SYSTEMS AND METHODS FOR DISPLAYING IN-FLIGHT NAVIGATION PROCEDURES

The Boeing Company, Chic...

1. A computing device for displaying procedures for an aircraft, said computing device comprising:
a presentation interface;
a user input interface; and
a processing device coupled to said presentation interface and to said user input interface, said processing device configured
to:

cause said presentation interface to display an initial procedure display that includes information for a plurality of procedures
that include at least one of an initial approach procedure, an intermediate approach procedure, a final approach procedure,
and a missed approach procedure; and

in response to a triggering event, cause said presentation interface to display an adjusted procedure display that emphasizes
a predetermined portion of one procedure of the plurality of procedures by excluding information included in the initial procedure
display for other procedures of the plurality of procedures and by automatically adjusting a scale of an overhead view relative
to the initial procedure display by resizing and centering the predetermined portion, wherein the adjusted procedure display
is distinct from an aircraft navigational display, and wherein the procedure is part of one of a standard instrument departure
and a standard terminal arrival route.

US Pat. No. 9,292,180

LOCATOR SYSTEM FOR THREE-DIMENSIONAL VISUALIZATION

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
an object manager configured to
identify a part in an aircraft;
generate a series of views from a model of the aircraft with graphical indicators in the series of views configured to provide
guidance to a position of the part in the aircraft;

display the series of views on a display device; and
display a view of a volume in the model of the aircraft corresponding to a physical position and a physical orientation of
the display device with a graphical indicator indicating a direction to the position of the part when the part is absent from
the view displayed on the display device;

wherein a visualization data system creates the model as a visualization model from a computer-aided design model such that
the visualization model includes only portions of the computer-aided design model needed to visualize the computer-aided design
model;

wherein a format of the information in the visualization model is selected to increase a speed at which a portion of the aircraft
is displayed on the display device;

wherein metadata used to enable editing of the computer-aided design model is removed from the visualization model; and
wherein the visualization model is stored in a data depot that is a storage system specific to a particular line for the aircraft.

US Pat. No. 9,199,295

ROLLER SWAGE METHOD AND APPARATUS

THE BOEING COMPANY, Chic...

1. An apparatus for roller swaging, the apparatus comprising:
a support arm having a radial component and an axial component;
a spherical roller attached to an end of the axial component of the support arm for relative rotational movement;
a mount slidably supporting the radial component of the support arm for movement of the radial component and the axial component
in a radial direction relative to a central axis of rotation of the mount;

a first actuator mounted on the mount for displacing the radial component and the axial component of the support arm relative
to the mount;

a linear slide;
a second actuator mounted on the linear slide, the second actuator having an axle that supports the mount and imparts rotational
movement to the mount about the central axis of rotation in which the spherical roller describes a circular path;

a third actuator connected to the second actuator such that the third actuator displaces the second actuator in a linear direction
on the linear slide; and

a control connected to activate the third actuator to displace the second actuator along the linear slide to move the support
arm into an end of a tube, the second actuator to rotate the mount, causing the support arm to describe a circular path, and
the first actuator to cause the support arm to travel in a radial direction outwardly from the central axis of rotation to
bring the spherical roller into contact with the tube to form an annular bulge in the tube.

US Pat. No. 9,183,419

PASSIVE RFID ASSISTED ACTIVE RFID TAG

The Boeing Company, Chic...

1. A radiofrequency identification (RFID) device comprising:
an active RFID tag that includes a power source and tag identification (TID) data unique to the active RFID tag;
a passive-RFID tag reader, the passive-RFID tag reader electrically coupled to the power source of the active RFID tag, wherein
the active RFID tag is configured to:

combine the TID data with data received from the passive-RFID tag reader into a combined data file; and
transmit the combined data file to an active tag reader; and
an optical detector electrically coupled to the active RFID tag and the passive-RFID tag reader, the optical detector configured
to:

optically detect a condition; and
output location data to the active RFID tag based on the optically detected condition.

US Pat. No. 9,174,723

SHAPE MEMORY ALLOY RODS FOR ACTUATION OF CONTINUOUS SURFACES

The Boeing Company, Chic...

1. An assembly for connecting two relatively movable structures on an aircraft, comprising:
first and second rigid structures;
a flexible skin connected to said first rigid structure and to said second rigid structure;
a first rod having a first end portion attached to said first rigid structure, said first rod comprising shape memory alloy
in at least an intermediate portion thereof;

a sleeve having first and second end portions; and
a second rod having a first end portion connected to said second rigid structure, said second rod comprising shape memory
alloy in at least an intermediate portion thereof,

wherein a second end portion of said first rod is slidably disposed inside said first end portion of said sleeve, and a second
end portion of said second rod is slidably disposed inside said second end portion of said sleeve.

US Pat. No. 9,091,230

LINKED RING PETAL ACTUATION FOR VARIABLE AREA FAN NOZZLE

The Boeing Company, Chic...

1. A variable area fan nozzle comprising:
a support member having a shape that is a circle or portion thereof, said support member being centered at an axis;
a movable member having a shape corresponding to the shape of said support member, said movable member being supported by
and movable along said support member, movement along said support member being a rotation of said movable member about said
axis;

a drive system capable of moving said movable member segment along said support member;
a cam attached to or integrally formed with said movable member;
a cam follower that is displaced along a straight line by said cam during rotational movement of said movable member along
said support member;

a push rod having a longitudinal axis and one end pivotably coupled to said cam follower for rotation about an axis perpendicular
to said longitudinal axis;

a petal link having one end pivotably coupled to an opposite end of said push rod; and
a petal pivotably coupled to said support member and to an opposite end of said petal link.

US Pat. No. 9,416,569

LATCH ASSEMBLY

THE BOEING COMPANY, Chic...

1. A latch assembly for use with a first structure having an outer surface and a second structure movable relative to the
first structure, the latch assembly comprising:
a latch member movable into and out of a latching position securing the second structure to the first structure;
a visual indicator device movable between a retracted position not protruding outward from the outer surface of the first
structure and an extended position protruding outward from the outer surface, the visual indicator device having a longitudinal
axis and movable longitudinally between the retracted position and the extended position and the latch member movable out
of the latching position pivotally about the longitudinal axis of the visual indicator device; and

a linkage that is operatively connected between the latch member and the visual indicator device to move the visual indicator
device from the retracted position to the extended position under the influence of the latch member when the latch member
is moved out of the latching position, the linkage comprising a helical cam and a cam follower engaged between the latch member
and the visual indicator device to move the visual indicator device longitudinally upon movement of the latch member pivotally.

US Pat. No. 9,393,516

SYSTEM AND METHOD FOR PRODUCING CARBON DIOXIDE

The Boeing Company, Chic...

1. A system for producing carbon dioxide comprising:
a collection subsystem configured to collect a process gas from a source, said process gas comprising a hydrocarbon;
a combustion subsystem configured to combust said hydrocarbon in said process gas and output a gaseous combustion effluent,
wherein said gaseous combustion effluent comprises carbon dioxide and water; and

a separation subsystem comprising:
a heat exchanger positioned to receive said gaseous combustion effluent and remove heat therefrom, thereby condensing a portion
of said water in said gaseous combustion effluent, said heat exchanger outputting a cooled gas;

a desiccant material positioned to contact said cooled gas and remove an additional quantity of said water therefrom, thereby
yielding a dried gas;

an adsorbent material positioned to contact said dried gas and adsorb at least a portion of said carbon dioxide, wherein said
adsorbent material is housed in a contact chamber;

a heat transfer assembly configured to collect said heat removed by said heat exchanger and transfer said heat to at least
one of said desiccant material and said adsorbent material; and

a vacuum source selectively fluidly coupled with said contact chamber.

US Pat. No. 9,336,588

JOINT ASSEMBLIES AND METHOD OF INSPECTING THEREOF

The Boeing Company, Chic...

1. A joint assembly comprising:
a first component comprising a first bond surface; and
a second component comprising a second bond surface coupled to said first bond surface such that a bond line is defined therebetween,
wherein at least one of said first and second components comprises a plurality of contrast particles that diffuse across said
bond line when a predetermined amount of heat and pressure are applied to said first and second components.

US Pat. No. 9,316,617

APPARATUS AND METHOD FOR EDDY CURRENT INSPECTION OF STRUCTURES

The Boeing Company, Chic...

1. A probe apparatus comprising:
a first end configured to connect to a rotating scanner device; and,
a second end comprising:
two or more eddy current elements comprising at least one reference eddy current coil and at least one test eddy current coil;
a positioning mechanism configured to position the two or more eddy current elements against cavity walls of an annular cavity
of a structure to be inspected with the probe apparatus, when the probe apparatus is positioned within the annular cavity;

an aligning mechanism coupled to the positioning mechanism, the aligning mechanism configured to align the two or more eddy
current elements in a perpendicular position with respect to the cavity walls of the annular cavity, when the probe apparatus
is positioned within the annular cavity; and

three or more foot portions, each foot portion attached to the positioning mechanism and attached to the aligning mechanism,
and each foot portion comprising a mounting element and a base element, the mounting element having a first side attached
to one eddy current element and having a second side attached to the base element.

US Pat. No. 9,296,471

SWING WING TIP SYSTEM, ASSEMBLY AND METHOD WITH DUAL LOAD PATH STRUCTURE

The Boeing Company, Chic...

1. A swing wing tip system for an air vehicle, the system comprising:
a swing wing tip assembly comprising:
an unfixed wing tip portion movably connected to a fixed wing portion of a wing of an air vehicle;
a dual load path structure providing two separate load bearing paths comprising dual wing skins and a rotation joint to carry
load in a fail-safe manner, and the dual load path structure configured to transfer load from the unfixed wing tip portion
to the fixed wing portion, the dual load path structure comprising:

dual wing skin plates comprising an upper wing skin with a separate plate portion attached to the upper wing skin and comprising
a lower wing skin with another separate plate portion attached to the lower wing skin, the separate plate portions being flush
with the respective upper wing skin and the lower wing skin; and

the rotation joint coupled between the dual wing skins and configured to rotationally couple the unfixed wing tip portion
to the fixed wing portion, the dual wing skins positioned across both sides of the rotation joint, the rotation joint comprising:

a dual rotation pin element having a center rotation axis; and,
dual rotation elements configured to rotate about the center rotation axis;
an actuator assembly operatively coupled to the rotation joint to actuate the rotation joint enabling rotation of the unfixed
wing tip portion with respect to the fixed wing portion about the center rotation axis at a selected operation condition;
and,

a controller system operatively coupled to the actuator assembly to control actuation of the rotation joint and rotation of
the unfixed wing tip portion.

US Pat. No. 9,267,782

GENERATING AN IMAGE USING AN ACTIVE OPTICAL INTERFERENCE SYSTEM

The Boeing Company, Chic...

1. A system, comprising:
a synthetic optical aperture configured to receive a plurality of received photon beams comprising a scene including an object;
an active optical interference system configured to interfere each of the plurality of received photon beams from the synthetic
optical aperture with a corresponding source photon beam of a plurality of source photon beams, the active optical interference
system generating a plurality of enhanced interference beams, each enhanced interference beam comprising at least a predetermined
increase in gain; and

a detector system configured to detect the plurality of enhanced interference beams and generate an electrical output signal
for use in generating a reconstructed image of the object with improved resolution responsive to at least the predetermined
increase in gain of the enhanced interference beams.

US Pat. No. 9,253,565

SYSTEM AND CHARACTERIZATION OF NOISE SOURCES USING ACOUSTIC PHASED ARRAYS AND TIME SERIES CORRELATIONS

The Boeing Company, Chic...

1. A method for detecting the presence of a noise signal within a noise measurement field, where the noise measurement field
includes a noise signal emanating from a noise source at a specific known spatial location within the noise measurement field,
and where the noise signal is mixed with extraneous noise existing within the noise measurement field, the method comprising:
configuring a plurality of acoustic transducers arranged in first and second arrays to monitor the noise measurement field
at a plurality of spatially separated locations, and where the acoustic transducers of each of said first and second arrays
are configured such that a distance from each one of said acoustic transducers of each of said first and second arrays to
said specific known spatial location of said noise source is known or assumed, so as to be able to detect the presence of
noise at least at one specific, predetermined spatial location within the noise measurement field;

sampling outputs from said acoustic transducers to generate time series data for each of said first and second arrays; and
processing said time series data to identify whether said noise signal is present, said processing said time series data including
analyzing said time series data and obtaining an averaged time varying signal for each of said first and second arrays, said
averaged time varying signal from each of said first and second arrays having a characteristic that said noise signal emanating
from said specific known spatial location within said noise measurement field is reinforced, and further such that said extraneous
noise is substantially reduced or eliminated therefrom.

US Pat. No. 9,061,249

AIRCRAFT FUEL TANK FLAMMABILITY REDUCTION METHOD AND SYSTEM

THE BOEING COMPANY, Chic...

1. An aircraft fuel tank flammability reduction method comprising:
feeding pressurized air into an air separation module containing a carbon membrane, the air feed exhibiting a normal pressure
of no more than 55 psig and the carbon membrane containing at least 95 weight percent carbon;

contacting the carbon membrane with the air feed, permeating oxygen from the air feed through the carbon membrane, and producing
nitrogen-enriched air from the air separation module as a result of removing oxygen from the air feed; and

feeding the nitrogen-enriched air into the fuel tank on board the aircraft.

US Pat. No. 9,522,742

SHORT LANDING WARNING

The Boeing Company, Chic...

1. A method of warning pilots of short landings during a flight of an aircraft, the method comprising:
determining, by a terrain awareness and warning system (TAWS) operating on the aircraft that the aircraft is on approach to
a runway, wherein a runway threshold and a target runway location are associated with the runway;

receiving, by the TAWS from an inertial reference unit (IRU), a flight path vector (FPV) location of the aircraft based at
least in part on a projected landing location with respect to the runway;

receiving, by the TAWS from the IRU, a current airspeed of the aircraft;
issuing, by the TAWS, a landing short alert when the FPV location is at or before the runway threshold wherein the landing
short alert comprises at least one of the following:

a landing short caution alert when a current altitude of the aircraft is above a warning threshold line; and
a short landing and pull up warning alert when the current altitude of the aircraft is below the warning threshold line;
issuing, by the TAWS, an airspeed caution alert when the FPV location is between the runway threshold and the target runway
location and the current airspeed is below a landing short envelope; and

determining, by the TAWS, not to issue an alert when the TAWS determines that the FPV location is between the runway threshold
and the target runway location and that the current airspeed is at or above the landing short envelope;

wherein the warning threshold line is determined based on at least an upper limit of the landing short alert, a lower limit
of the airspeed caution alert, an activation distance of an envelope from runway threshold, a horizontal distance from the
aircraft to the runway threshold, and a horizontal distance from the aircraft to the FPV location.

US Pat. No. 9,508,134

APPARATUS, SYSTEM, AND METHOD FOR ENHANCING IMAGE DATA

The Boeing Company, Chic...

1. A method of enhancing image data, comprising:
transforming image data from an intensity domain to a wavelet domain to produce a plurality of wavelet coefficients, wherein
a first set of wavelet coefficients of the plurality of wavelet coefficients comprises low-frequency wavelet coefficients;

modifying the first set of wavelet coefficients using a coefficient distribution based filter to produce a modified first
set of wavelet coefficients, wherein modifying the first set of wavelet coefficients using the coefficient distribution based
filter comprises partitioning the first set of wavelet coefficients into a plurality of regions, calculating a coefficient
distribution for each region of the plurality of regions, modifying the coefficient distribution for each region, forming
a coefficient transformation function for each region, and modifying the first set of wavelet coefficients using the coefficient
transformation functions; and

transforming the modified first set of wavelet coefficients from the wavelet domain to the intensity domain to produce enhanced
image data.

US Pat. No. 9,291,147

SAIL-BASED ELECTRICAL GENERATION SYSTEM AND METHOD

THE BOEING COMPANY, Chic...

1. An energy generating system, comprising:
a first pair of sails, at least partially immersed in flowing water, configured for opposing reciprocal swinging motion in
response to a flow of fluid therepast; and

a first generator assembly, mechanically coupled to the first pair of sails, configured to generate electrical energy from
the opposing reciprocal swinging motion of the first pair of sails.

US Pat. No. 9,480,163

DIGITIZING SENSORS COUPLED TO A STRUCTURE

The Boeing Company, Chic...

1. A structure, comprising:
a structural element;
a digitizing sensor coupled to the structural element;
a bus comprising a plurality of conductive traces applied on the structural element using a direct-write technique, wherein
one or more power traces of the bus provide power to the digitizing sensor, and wherein one or more communication traces of
the bus enable data communication from the digitizing sensor;

a first conductive shield layer applied to the structural element, wherein the one or more communication traces are applied
over the first conductive shield layer; and

a first insulating layer between the first conductive shield layer and the one or more communication traces.

US Pat. No. 9,395,810

UBIQUITOUS NATURAL USER SYSTEM

The Boeing Company, Chic...

1. A ubiquitous natural user system comprising: one or more sensors configured to sense a user, an environment of the user
or an interaction of the user with the environment, and provide sensed input characteristic thereof, the sensors including
a three-dimensional scanner configured to provide measurements of points on a surface of an object in the environment, and
the sensed input including the measurements provided by the three-dimensional scanner; and
a front-end system coupled to the one or more sensors, the front-end system being configured to receive and process the sensed
input including the measurements to identify a known pattern that indicates a significance of the sensed input from which
to identify operations of one or more electronic resources, the front-end system being configured to process the sensed input
according to one or more intent algorithms using one or more information models or one or more historical intent-operation
associations,

wherein the front-end system is configured to form and communicate an input to cause the one or more electronic resources
to perform the operations, including generation of a point cloud from the measurements, and transformation of the point cloud
to a three-dimensional model of the object, and

wherein the front-end system is configured to receive an output including the three-dimensional model from the one or more
electronic resources, and communicate the output for display by a display device.

US Pat. No. 9,366,296

SWAGING FEATURES THAT LOCK RETAINING ELEMENTS FOR BEARINGS

The Boeing Company, Chic...

1. An apparatus comprising:
a bearing comprising:
an outer race having a first end and a second end, and wherein the race comprises:
a flange on the first end that is adapted to mate with a housing for the bearing;
an annular threaded portion on the second end, wherein the annular threaded portion is adapted to receive an annular threaded
retaining element that mates with the housing; and

an annular protrusion on the second end, concentric with the threaded portion, that is adapted to be swaged, to thereby increase
a diameter of the protrusion to overlap the threaded portion.

US Pat. No. 9,195,235

BEAM DIRECTED MOTION CONTROL SYSTEM

THE BOEING COMPANY, Chic...

1. A vehicle control system comprising:
a first energy source configured to generate a first beam of energy directed at a first area on a target for a vehicle;
a second energy source configured to generate a second beam of energy directed at a second area on the target;
a position system configured to identify a first position of the first area on the target at which the first beam of energy
is directed and a second position of the second area on the target at which the second beam of energy is directed; and

a movement system configured to simultaneously rotate the vehicle around a vertical axis through the vehicle and translate
the vehicle, respectively forming a rotation and a translation, in a combined manner that reduces a difference between the
first position of the first area at which the first beam of energy is directed, the second position of the second area at
which the second beam of energy is directed, and a reference position on the target, wherein the rotation and the translation
are movements independent of each other.

US Pat. No. 9,114,568

EXTRUSION OF ADHESIVES FOR COMPOSITE STRUCTURES

THE BOEING COMPANY, Chic...

1. A method comprising:
extruding an uncured flowable filler material onto a composite charge that is substantially flat, the uncured flowable filler
material comprises a stiffness sufficient to maintain a pre-determined cross section after extruding and prior to shaping
or curing;

forming the composite charge into a first composite member; and
assembling the first composite member and a second composite member.

US Pat. No. 9,090,043

MOLYBDENUM COMPOSITE HYBRID LAMINATES AND METHODS

The Boeing Company, Chic...

1. A molybdenum composite hybrid laminate comprising:
a plurality of composite material layers;
a plurality of surface treated molybdenum foil layers interweaved between the composite material layers; and,
a plurality of adhesive layers disposed between and bonding adjacent layers of the composite material layers and the molybdenum
foil layers,

wherein each of the plurality of surface treated molybdenum foil layers has a sufficient stiffness to leverage a fiber tensile
strength and a fiber stiffness of off-axis fibers in adjacent composite material layers via Poisson's effects in each of the
plurality of surface treated molybdenum foil layers.

US Pat. No. 9,086,522

DEVICES FOR COMMUNICATING OPTICAL SIGNALS AND ELECTRICAL SIGNALS OVER NANOTUBES

THE BOEING COMPANY, Chic...

1. An apparatus comprising:
a device configured to communicate using an optical signal and an electrical signal through a connection to a tube comprised
of a number of layers of carbon forming a wall of the tube, wherein the number of layers of carbon has a number of optical
properties configured to propagate the optical signal within a channel in the tube and a number of electrical properties configured
to conduct the electrical signal along a surface of the wall of the tube; and

the device comprising a circuit powered by a voltage difference that occurs as the electrical signal travels through the tube
and as a magnetic field is applied to the electric signal;

wherein the voltage difference is a Hall Effect voltage.

US Pat. No. 9,381,548

SYSTEMS FOR REMOVING LUBRICANTS FROM SUPERPLASTIC-FORMING OR HOT-FORMING DIES

The Boeing Company, Chic...

1. A method of cleaning a die having an oxide layer, the method comprising:
discharging electromagnetic energy towards a working surface of the die having a layer of at least one of graphite and boron
nitride thereon, wherein the electromagnetic energy is discharged at a power output between about 6 kW and about 15 kW such
that the layer of at least one of graphite and boron nitride is ablated, and such that the layer is removed without removing
an oxide layer between the surface of the die and the layer.

US Pat. No. 9,163,909

UNMANNED MULTI-PURPOSE GROUND VEHICLE WITH DIFFERENT LEVELS OF CONTROL

THE BOEING COMPANY, Chic...

1. A vehicle comprising:
a platform deployable by a deployment vehicle;
a propulsion system connected to the platform and configured to move the platform on a ground;
a sensor system connected to the platform and configured to generate sensor data; and
a computer system connected to the platform, wherein the computer system is configured to run a plurality of control processes
to perform a mission responsive to deployment of the vehicle by the deployment vehicle at a first location, and to perform
a corresponding plurality of operations in response to a corresponding plurality of commands from a plurality of operators;

wherein the computer system is further configured to direct movement of the vehicle along a series of mission-defined waypoints
to identify at least one mission objective;

wherein the computer system is further configured to receive a number of requests interrupting the mission to change control
of the vehicle from the plurality of control processes to the plurality of operators, determine whether the number of requests
is valid, perform the corresponding plurality of operations in response to the number of commands from the plurality of operators
if the number of requests is valid, and return control of the vehicle from the plurality of operators to the plurality of
control processes for resumption of the mission, wherein ones of the plurality of operators control different ones of the
plurality of control processes such that a given operator controls a different control process relative to another operator,
and wherein the plurality of operators are human operators; and

wherein the computer system is further configured, upon completion of the mission, to direct movement of the vehicle to a
second location for retrieval by the deployment vehicle.

US Pat. No. 9,127,971

NON-DESTRUCTIVE INSPECTION SYSTEMS AND METHODS THAT INCORPORATE INTERCHANGEABLE PROBES

The Boeing Company, Chic...

1. A non-destructive inspection (NDI) device comprising:
a robotic arm;
a storage device proximate said robotic arm; and
a plurality of NDI probe assemblies disposed within said storage device, each NDI probe assembly comprising at least one transducer
operable for NDI of a part and a tool operable as a mechanical interface between said robotic arm and the corresponding said
NDI probe assembly, each said NDI probe assembly configured for a specific NDI task, for NDI of a part, said robotic arm operable
for selectively engaging said tools and movement of said probe assemblies for the NDI of at least a portion of a part; and

an outside magnetic guidance fixture comprising:
a first probe assembly half;
a second probe assembly half; and
at least one guide bar utilized to mechanically connect said probe assembly halves, said second probe assembly half being
movable with respect to said first probe assembly half, each said probe assembly half comprising at least one magnet disposed
therein, said magnets operable to move said second probe assembly half such that said NDI probe assembly engages the portion
of the part that is to undergo NDI.

US Pat. No. 9,986,660

CONDUCTION COOLED AUTONOMOUS GIMBALED INERTIAL MEASUREMENT UNIT

The Boeing Company, Chic...

1. An apparatus comprising:an inertial measurement unit;
a gimbal assembly in which the inertial measurement unit is disposed, the gimbal assembly having gaps between each gimbal of the gimbal assembly, the gaps sized to reduce convective heat transfer and facilitate conductive heat transfer between each gimbal, the gaps including a gas to conduct heat from the gimbal assembly; and
an isothermal dome at least partially surrounding the gimbal assembly, the isothermal dome having a cooling tube disposed on an external surface of the isothermal dome to transfer heat from the gimbal assembly via conduction.

US Pat. No. 9,262,928

PREDICTION OF FLIGHT PATH PRIVACY

The Boeing Company, Chic...

1. A method of predicting an achievable level of privacy of a flight path, the method comprising:
receiving, by a computer comprising a processor and memory, an indication of a flight route of an aircraft;
receiving, by the computer, an indication of one or more privacy enhancement techniques;
estimating, by the computer, an air traffic density for one or more airspaces along or near the flight route, the estimating
based on information obtained from one or more aviation information databases;

estimating, by the computer, an achievable level of privacy of the flight path based, at least in part, on the air traffic
density for one or more airspaces and the one or more privacy enhancement techniques; and

outputting, to a display communicatively coupled to the computer, an indication of the estimated achievable level of privacy.

US Pat. No. 9,193,483

METHOD OF FORMING A WINDOW CUTOUT IN AN AIRFRAME

The Boeing Company, Chic...

1. A method of forming cutouts in an aircraft fuselage, comprising the steps of:
forming a first cutout and a second cutout in side-by-side relation to one another in a side region of a fuselage, the side
region including a single skin formed as a laminate of composite material having a plurality of reinforcing fibers embedded
within a matrix;

configuring the first cutout and the second cutout such that a direct load path extends along the side region substantially
continuously from a lower portion of the side region generally under the first cutout to an upper portion of the side region
generally over the second cutout; and

orienting the reinforcing fibers substantially parallel to the direct load path along a spiral direction from the lower portion
to the upper portion.

US Pat. No. 9,157,746

VESSEL ROUTING SYSTEM

The Boeing Company, Chic...

1. A method for routing a vessel from a start point to an end point, the method comprising:
generating on a processor a plurality of routes from the start point to the end point over an ocean based on a number of objectives,
the number of objectives including at least arrival time and fuel usage of the vessel;

determining on the processor whether the plurality of routes include segments that cross a region of interest;
responsive to a segment between two waypoints in a route in the plurality of routes crossing a region of interest, generating
on the processor a plurality of groups of waypoints around the region of interest, the plurality of groups of waypoints defining
a number of segments including at least a first segment and a second segment, each of the number of segments providing a route
with respect to the region of interest;

determining on the processor a predicted performance for each of the number of segments based on at least two of the number
of objectives including the arrival time and the fuel usage;

identifying a set of segments, from the number of segments, comprising potential routes from the number of segments, the set
of segments in the potential routes selected for dominating the number of segments for both fuel usage and arrival time such
that the values for arrival time in the set of segments and the set of values for fuel usage are at least equal to or better
than those values for the other routes in the number of segments;

incrementing a variable for the number of segments that has been dominated by another set of segments so as to form an incremented
variable, the incremented variables including at least wind and current;

performing a second evaluation of the number of segments with variables that have been incremented;
selecting a segment from among the set of segments to form a selected segment, the selected segment based on the number of
objectives and the incremented variables; adding one of the selected segment from the set of segments to the route between
the start point and the end point so as to add a group of waypoints between two waypoints in the route with respect to the
region of interest; and

routing the vessel from the start point to the end point using the group of waypoints.