The Boeing Company

United States of America

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IPC Class
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor 137
B64D 47/00 - Equipment not otherwise provided for 66
B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for 62
B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like 59
B64C 1/12 - Construction or attachment of skin panels 54
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1.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Document Number 03080914
Status Pending
Filing Date 2020-05-19
Open to Public Date 2020-11-20
Owner THE BOEING COMPANY (USA)
Inventor
  • Clark, Adam M.
  • Bays-Muchmore, C. Byram
  • Konings, Christopher Andrew
  • Phung, Connie
  • Goering, Daniel Joseph
  • Robinson, Miles Anthony
  • Vijgen, Paul M.
  • Philipp, Paul Brian
  • Dodt, Thomas K.

Abstract

Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine coupled to a nacelle. The chine is oriented along a fore-aft direction. The chine is translatable relative to the nacelle along the fore-aft direction.

IPC Classes  ?

  • B64C 7/00 - Structures or fairings not otherwise provided for
  • B64C 5/12 - Stabilising surfaces adjustable for retraction against or within fuselage or nacelle

2.

FASTENER SYSTEMS AND ASSEMBLIES FOR COUPLING A PART TO A COMPOSITE STRUCTURE, AND RELATED METHODS

      
Document Number 03081031
Status Pending
Filing Date 2020-05-20
Open to Public Date 2020-11-20
Owner THE BOEING COMPANY (USA)
Inventor Rohlinger, Paul L.

Abstract

Fastener systems may be used to couple a part to a composite structure such that at least a portion of the fastener system is embedded within the composite structure, and such that the fastener system may be installed via access to just one side of the composite structure. Examples of fastener systems include a receptacle that is inserted through at least one layer of the composite structure and a torque nail that is inserted into the receptacle, thereby expanding the receptacle into a collar plate, which is configured to distribute the forces from insertion of the torque nail. The collar plate is enclosed between respective laminates of the composite structure, such that the fastener system is configured to couple the part to the composite structure, either directly or via a structural connector, without the use of conventional drilling and bolting.

IPC Classes  ?

  • F16B 17/00 - Fastening means without screw-thread for connecting constructional elements or machine parts by a part of or on one member entering a hole in the other

3.

METHOD OF TESTING ADDITIVE MANUFACTURED MATERIAL AND ADDITIVE MANUFACTURED PARTS

      
Document Number 03077782
Status Pending
Filing Date 2020-04-09
Open to Public Date 2020-11-16
Owner THE BOEING COMPANY (USA)
Inventor
  • Meier, Stefanie Anita
  • Rodriguez, Rogie I.
  • Park, Chul Young
  • Haworth, Troy Allan

Abstract

Methods of using micro-specimens for testing an additive manufactured material or a part made from the additive manufactured material. The methods include testing small and large test specimens taken from an additive manufactured part and from a blank constructed from the additive manufactured material. Correction factors based on the test specimens are calculated and applied to a calculated material property of the additive manufactured material.

IPC Classes  ?

  • G01N 37/00 - INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES - Details not covered by any other group of this subclass
  • B33Y 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
  • B33Y 80/00 - Products made by additive manufacturing
  • B33Y 40/20 - Post-treatment, e.g. curing, coating or polishing
  • G01N 3/00 - Investigating strength properties of solid materials by application of mechanical stress

4.

SYSTEM FOR DETERMINING THE STACK CLOSURE PRESSURE OF A BRAKE STACK

      
Document Number 03077639
Status Pending
Filing Date 2020-04-07
Open to Public Date 2020-11-13
Owner THE BOEING COMPANY (USA)
Inventor
  • Yamamoto, David T.
  • Smith, Steven Elliot
  • Forghani, Nima

Abstract

A brake system is disclosed. The brake system includes a brake stack having a stack closure pressure, a force member positioned within a cylinder, a valve configured to control the fluid pressure of the brake system, and one or more pressure transducers that generate a proportional electrical signal representative of fluid pressure within the cylinder. The brake system also includes one or more processors in electronic communication with the valve, the one or more pressure transducers, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the brake system to determine the stack closure pressure of the brake stack.

IPC Classes  ?

  • B60T 17/22 - Devices for monitoring or checking brake systems; Signal devices
  • B64C 25/44 - Actuating mechanisms
  • F16D 65/14 - Actuating mechanisms for brakes; Means for initiating operation at a predetermined position

5.

FASTENER AND METHODS OF MANUFACTURING AND USE

      
Document Number 03074553
Status Pending
Filing Date 2020-03-03
Open to Public Date 2020-11-10
Owner THE BOEING COMPANY (USA)
Inventor Simpson, Blake A.

Abstract

The present disclosure provides a fastener. The fastener includes an elongated body having a first end and a second end opposite the first end. The fastener also includes a head having a first surface and a second surface opposite the first surface. The first end of the elongated body is coupled to the second surface of the head, and a diameter of the head is greater than a diameter of the elongated body. The fastener also includes a sleeve positioned over at least a portion of the elongated body and the second surface of the head. The fastener also includes a plurality of textured elements positioned on an exterior surface of the sleeve adjacent the second surface of the head. One or more of the plurality of textured elements extend from the exterior surface of the sleeve to the first surface of the head.

IPC Classes  ?

  • F16B 39/282 - Locking by means of special shape of work-engaging surfaces, e.g. notched or toothed nuts

6.

SYSTEMS AND METHODS FOR AUTOMATED INTRUSION DETECTION

      
Document Number 03078658
Status Pending
Filing Date 2020-04-17
Open to Public Date 2020-11-10
Owner THE BOEING COMPANY (USA)
Inventor Ahluwalia, Rajpreet Singh

Abstract

Implementations provide automated intrusion alert-based blacklisting with minimal false positives that ignores regular business operations, scalable to accommodate the volume of IDS alerts received by high-traffic internet-accessible networked systems. Implementations identify and block hostile infrastructure IP addresses during the reconnaissance phase based on IDS alert(s). Each IDS alert is automatically reviewed in historical context and triggers IP blocking as necessary. Some implementations maintain TCP/IP handshake records, preventing blocking an IP used to conduct regular business operations on the network that a malicious party has spoofed to avoid identification. Based on the historical context of each IP address within the local network environment, specifically regular business operations traffic versus malicious traffic, the IP address is blocked only if the majority of connections therefrom are malicious. This approach provides substantial cost-savings; frees up resources and personnel otherwise necessary for manual processes; and increases overall network security through automated network defense.

IPC Classes  ?

  • H04L 12/22 - Arrangements for preventing the taking of data from a data transmission channel without authorisation
  • G06F 21/55 - Detecting local intrusion or implementing counter-measures

7.

COMPOSITE STRUCTURE HAVING A VARIABLE GAGE AND METHODS FOR FORMING A COMPOSITE STRUCTURE HAVING A VARIABLE GAGE

      
Document Number 03080607
Status Pending
Filing Date 2020-05-06
Open to Public Date 2020-11-09
Owner THE BOEING COMPANY (USA)
Inventor Cheng, Jiangtian

Abstract

In an example, a composite structure having a variable gage is described. The composite structure includes a first end having a first gage, a second end having a second gage, which is less than the first gage, a plurality of continuous plies, and a plurality of drop-off plies. Each continuous ply extends from the first end to the second end. Each drop-off ply includes a tip having a tapered shape. Each drop-off ply extends from the first end to a respective position of the tip of the drop-off ply between the first end and the second end. The plurality of drop-off plies are separated from each other by at least one of the plurality of continuous plies.

IPC Classes  ?

  • B32B 3/02 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by features of form at particular places, e.g. in edge regions
  • B32B 3/26 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids
  • B32B 37/14 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the properties of the layers

8.

COMPOSITE STRINGER AND METHODS FOR FORMING A COMPOSITE STRINGER

      
Document Number 03084624
Status Pending
Filing Date 2020-05-06
Open to Public Date 2020-11-09
Owner THE BOEING COMPANY (USA)
Inventor Cheng, Jiangtian

Abstract

In an example, a composite stringer is described. The composite stringer includes a skin flange having a first gage, a top flange having a second gage, and a web having a third gage and extending between the skin flange and the top flange. The skin flange is configured to be coupled to a support structure. The support structure includes at least one of a skin of a vehicle or a base charge. The second gage of the top flange is greater than the first gage of the skin flange and the third gage of the web. The skin flange, the top flange, and the web include a plurality of plies of composite material.

IPC Classes  ?

  • B64C 1/06 - Frames; Stringers; Longerons
  • B29C 70/30 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
  • B64C 3/18 - Spars; Ribs; Stringers

9.

CARGO AERIAL DELIVERY SYSTEMS AND RELATED METHODS

      
Document Number 03073620
Status Pending
Filing Date 2020-02-24
Open to Public Date 2020-11-09
Owner THE BOEING COMPANY (USA)
Inventor Polus, Jeffrey Edward

Abstract

Cargo aerial delivery systems for delivering one or more delivery items and related methods. A cargo aerial delivery system may include a cargo container configured to carry the delivery item(s) and an unmanned aerial vehicle (UAV) configured to carry the cargo container to delivery destinations of the delivery items. The cargo container may include a programmable device that stores manifest information regarding the delivery item(s) and a local communication mode configured to convey delivery information from the cargo container to the UAV. A method of utilizing a cargo aerial delivery system may include loading delivery item(s) into a container body of a cargo container, entering manifest information into a programmable device, operatively engaging the cargo container with a UAV, generating a delivery itinerary, transporting the cargo container with the UAV according to the delivery itinerary, and unloading each delivery item at the respective delivery destination.

IPC Classes  ?

  • G06Q 10/08 - Logistics, e.g. warehousing, loading, distribution or shipping; Inventory or stock management, e.g. order filling, procurement or balancing against orders
  • G06Q 50/30 - Transportation; Communications
  • B64C 39/02 - Aircraft not otherwise provided for characterised by special use
  • B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
  • B65D 88/14 - Large containers rigid specially adapted for transport by air

10.

METHOD OF CONTROLLING PARTICLES SIZE OF FILLERS IN EXTRUDABLE COMPOSITIONS, COMPOSITIONS COMPRISING THE FILLERS AND DEVICES MADE FROM THE COMPOSITIONS

      
Document Number 03074356
Status Pending
Filing Date 2020-03-02
Open to Public Date 2020-11-06
Owner THE BOEING COMPANY (USA)
Inventor
  • Bruton, Eric Alan
  • Shawgo, Loyal Bruce

Abstract

A method of controlling a particle size distribution of a filler in an extrudable composition comprises introducing an extrudable composition comprising a polymer matrix material and a filler into an extruder, the filler having a first average particle size that is larger than a target average particle size. The extrudable composition is extruded one or more times using the extruder to reduce the size of the filler from the first average particle size to a reduced average particle size, the reduced average particle size being within 10% of the target average particle size.

IPC Classes  ?

  • C08K 3/013 - Fillers, pigments or reinforcing additives
  • B29C 48/92 - Measuring, controlling or regulating
  • B29C 70/58 - Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising fillers only
  • C08J 3/20 - Compounding polymers with additives, e.g. colouring
  • C08L 101/00 - Compositions of unspecified macromolecular compounds

11.

DETERMINING SERVICABILITY AND REMAINING LIFE OF AN IN-SERVICE STRUCTURE USING THREE-DIMENSIONAL SCAN DATA

      
Document Number 03073249
Status Pending
Filing Date 2020-02-20
Open to Public Date 2020-11-03
Owner THE BOEING COMPANY (USA)
Inventor
  • Brown, Thomas A.
  • Farniok, Craig Martin
  • Roffo, Todd
  • Smith, Nicholas E.
  • Thilges, Jacob Paul

Abstract

According to an example, three-dimensional (3D) scan data representative of an in-service structure that is captured by a scanning device is accessed by a processor circuit. Based on the 3D scan data, in-service computer-aided design (CAD) data representative of an in-service surface corresponding to the in- service structure is generated by the processor circuit. Based on the in-service CAD data representative of the in-service surface, at least one of a serviceability level or remaining life estimate of the in-service structure is determined.

IPC Classes  ?

  • G01B 21/20 - Measuring arrangements or details thereof in so far as they are not adapted to particular types of measuring means of the other groups of this subclass for measuring contours or curvatures, e.g. determining profile
  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • G06F 30/10 - Geometric CAD
  • G06F 30/20 - Design optimisation, verification or simulation

12.

AIRCRAFT HAVING FOLDABLE WINGS

      
Document Number 03070845
Status Pending
Filing Date 2020-02-03
Open to Public Date 2020-11-03
Owner THE BOEING COMPANY (USA)
Inventor
  • Good, Mark Steven
  • Walker, Steven Paul

Abstract

Aircrafts having foldable wings are disclosed. An example aircraft includes a fixed wing portion, a foldable wing tip, and a hinge interface to pivotally couple the foldable wing tip and the fixed wing portion. The hinge interface has a first hinge defining a hinge axis that is substantially parallel to a fuselage centerline. The first hinge has a first dimension in a spanwise direction and a second dimension in a chordwise direction. The first dimension is greater than the second dimension.

IPC Classes  ?

  • B64C 3/56 - Folding or collapsing to reduce overall dimensions of aircraft
  • B64C 5/08 - Stabilising surfaces mounted on, or supported by, wings

13.

ONE PIECE MULTIFUNCTIONAL NANOLAMINATED COMPOSITE WINDOW PANE

      
Document Number 03079589
Status Pending
Filing Date 2020-04-27
Open to Public Date 2020-11-02
Owner THE BOEING COMPANY (USA)
Inventor
  • Cheng, Jiangtian
  • Nordman, Paul S.

Abstract

One piece, multifunctional window assemblies for use in vehicles, equipment, or structures and methods for making them is provided. The disclosed window assembly can include a protection panel and a structural panel each formed of a plurality of nanolaminated layers. The nanolaminated window assembly is self-supporting and does not need a frame. For particular applications, such as in an aircraft, the one piece, multifunctional, nanolaminated window can be directly attached to the fuselage to provide load bearing capability, a larger window area, impact protection, ice buildup prevention, and/or electromagnetic effect protection.

IPC Classes  ?

  • B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
  • E06B 3/66 - Units comprising two or more parallel glass or like panes in spaced relationship, the panes being permanently secured together, e.g. along the edges
  • E06B 5/00 - Doors, windows, or like closures for special purposes; Border constructions therefor

14.

REMOVABLE BATTERY COMPRESSION DEVICES

      
Document Number 03074058
Status Pending
Filing Date 2020-02-26
Open to Public Date 2020-10-30
Owner THE BOEING COMPANY (USA)
Inventor Bernhardt, Roger D.

Abstract

Certain aspects of the present disclosure provide a vehicle, comprising: a housing; a battery comprising a plurality of layers and disposed within the housing; and a first removable battery compression device disposed within the housing and configured to apply compressive force to the plurality of layers of the battery via a first side of the battery.

15.

LOGIC CONTROL FOR AUTONOMOUSLY AND MANUALLY LOCKING OVERHEAD BINS FOR ENHANCED SAFETY

      
Document Number 03074554
Status Pending
Filing Date 2020-03-04
Open to Public Date 2020-10-29
Owner THE BOEING COMPANY (USA)
Inventor Chengalva, Mahesh

Abstract

A control system and method of controlling access to storage bins in a vehicle. The system includes a lock configured to be selectively movable between a locked position to prevent access to an interior of the storage bins and an unlocked position to allow access to the interior of the storage bins. A switch is positioned in a cabin of the vehicle. A control circuit is configured to determine an operational status of the vehicle and selectively position the locks. The control circuit can also receive an override signal from the switch and unlock the locks in certain situations.

IPC Classes  ?

  • B64D 25/00 - Emergency apparatus or devices, not otherwise provided for
  • E05F 15/611 - Power-operated mechanisms for wings using electrical actuators using rotary electromotors for swinging wings
  • E05F 15/72 - Power-operated mechanisms for wings with automatic actuation responsive to emergency conditions, e.g. fire
  • B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
  • G05B 19/045 - Programme control other than numerical control, i.e. in sequence controllers or logic controllers using logic state machines, consisting only of a memory or a programmable logic device containing the logic for the controlled machine and in which the state of its outputs is dependent on the state of its inputs or part of its own output states, e.g

16.

SELF-CONTAINED COOLING DEVICE FOR AN ELECTROMAGNETIC INTERFERENCE FILTER

      
Document Number 03073547
Status Pending
Filing Date 2020-02-21
Open to Public Date 2020-10-25
Owner THE BOEING COMPANY (USA)
Inventor
  • Messer, Timothy D.
  • Williams, John Dalton

Abstract

A cooling device for an electromagnetic interference filter is disclosed. The cooling device includes a housing. The housing includes a main body having a cavity shaped to receive the electromagnetic interference filter and one or more cooling channels surrounding at least a portion of the cavity in the main body of the housing. The one or more cooling channels define one or more flow paths that are contained completely within the housing. The housing also includes an inlet port and an outlet port. The one or more cooling channels fluidly connect the inlet port to the outlet port, and a cooling medium is configured to flow into the inlet port, through the one or more cooling channels, and exit the housing through the outlet port.

IPC Classes  ?

  • H05K 7/20 - Modifications to facilitate cooling, ventilating, or heating
  • H03H 7/01 - Frequency selective two-port networks

17.

ALIGNING SENSORS ON VEHICLES USING SENSOR OUTPUT

      
Document Number 03076342
Status Pending
Filing Date 2020-03-19
Open to Public Date 2020-10-24
Owner THE BOEING COMPANY (USA)
Inventor
  • Callahan, Kevin S.
  • Evans, Nick S.
  • Muir, Eric R.

Abstract

Systems and methods of aligning removable sensors mounted on a vehicle based upon sensor output of such sensors are described. Sensor output is collected from a removable sensor (e.g., a digital camera), and a representation of such sensor output is generated (e.g., a digital image). The representation of the sensor output is compared against a spatial template (e.g., a digital mask overlaid on the representation) to determine whether external references in the representation align with corresponding reference indicators in the spatial template. When alignment is required, the removable sensor is aligned by one or both of the following until the external references in a representation of sensor data at an updated current location align with the corresponding reference indicators in the spatial template: (i) adjusting the position of the removable sensor on the vehicle or (ii) adjusting the representation of the sensor output to simulate such repositioning.

IPC Classes  ?

  • G01B 21/24 - Measuring arrangements or details thereof in so far as they are not adapted to particular types of measuring means of the other groups of this subclass for testing the alignment of axes for testing the alignment of axes
  • B60S 5/00 - Servicing, maintaining, repairing, or refitting of vehicles
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
  • G01S 7/497 - Means for monitoring or calibrating

18.

METHOD, SYSTEM AND APPARATUS FOR ALIGNING A REMOVABLE SENSOR ON A VEHICLE

      
Document Number 03077438
Status Pending
Filing Date 2020-03-30
Open to Public Date 2020-10-24
Owner THE BOEING COMPANY (USA)
Inventor
  • Callahan, Kevin S.
  • Evans, Nick S.
  • Muir, Eric R.

Abstract

A method for aligning a removable sensor on a vehicle includes connecting the removable sensor to a sensor mounting device. The method further includes connecting a connector of an alignment apparatus to either (i) the removable sensor such that a spatial reference component of the alignment apparatus has a known position and orientation relative to a current position and orientation of the removable sensor or (ii) a fixed connection location on the vehicle such that the spatial reference component indicates a desired position and orientation of the removable sensor. In addition the method includes adjusting the current position and orientation of the removable sensor by reference to the alignment apparatus to cause the current position and orientation of the removable sensor to match the desired position and orientation of the removable sensor.

IPC Classes  ?

  • G01D 18/00 - Testing or calibrating apparatus or arrangements provided for in groups
  • B64D 45/04 - Landing aids; Safety measures to prevent collision with earth's surface
  • B64D 47/00 - Equipment not otherwise provided for
  • B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
  • F16M 13/00 - Other supports for positioning apparatus or articles; Means for steadying hand-held apparatus or articles
  • G01D 11/16 - Elements for restraining or preventing the movement of parts, e.g. for zeroising

19.

TOOL HEAD ASSEMBLY FOR SOLID STATE ADDITIVE MANUFACTURING

      
Document Number 03076965
Status Pending
Filing Date 2020-03-25
Open to Public Date 2020-10-22
Owner THE BOEING COMPANY (USA)
Inventor Verma, Ravi

Abstract

A tool head assembly for a solid state additive manufacturing apparatus includes a tool head having a material passage configured to receive a material therein. The tool head is configured to deposit the material from the material passage onto a substrate of the solid state additive manufacturing apparatus to form at least one layer of the material on the substrate. The tool head includes a shoulder configured to contact the material such that rotation of the tool head frictionally stirs the material. The tool head assembly includes a barrier configured to extend along a side surface of the at least one layer as the at least one layer is deposited onto the substrate such that the barrier is configured to constrain the material from extruding past an edge of the shoulder.

IPC Classes  ?

  • B29C 64/205 - Means for applying layers
  • B33Y 10/00 - Processes of additive manufacturing
  • B33Y 30/00 - ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING - Details thereof or accessories therefor
  • B33Y 40/00 - Auxiliary operations or equipment, e.g. for material handling
  • B29C 64/141 - Processes of additive manufacturing using only solid materials

20.

SYSTEM AND METHOD FOR HANDLING TERRAIN IN DETECT AND AVOID

      
Document Number 03069370
Status Pending
Filing Date 2020-01-22
Open to Public Date 2020-10-18
Owner THE BOEING COMPANY (USA)
Inventor Estkowski, Regina Inez

Abstract

Object detection and avoidance comprising receiving time-referenced position and state data for vehicles, including a control vehicle, within a specified time-space zone, wherein the vehicles have initial positions within the specified time- space zone. Terrain data is received for a spatial zone of interest that overlaps the time- space zone. A trajectory window is calculated for each vehicle within the time-space zone, as well as spatial buffer zones around terrain in the spatial zone of interest according to data uncertainty and resolution. A number of homotopically distinct paths are calculated for the control vehicle from a time-referenced initial position to a destination point, wherein the paths keep the control vehicle at least a minimum specified distance from the trajectory windows of other vehicles and the buffer zones of terrain and obstacles. The control vehicle is then routed according to one of the paths.

IPC Classes  ?

21.

ENHANCED AUTOBRAKE SELECTION INTERFACE

      
Document Number 03075241
Status Pending
Filing Date 2020-03-11
Open to Public Date 2020-10-18
Owner THE BOEING COMPANY (USA)
Inventor
  • Verhaeghe, Anna K.
  • Yamamoto, David T.

Abstract

An autobrake selection interface for an aircraft includes a cockpit mounted user selectable display. The display includes autobrake selection options and braking information. The autobrake selection options include at least one of an autobrake off option, a rejected takeoff (RTO) option, a constant deceleration option, and a runway exit selection option. The braking information includes at least one of an estimated brake temperature, an estimated brake cooling time, and an estimated landing distance. The autobrake selection interface also includes a braking parameters determiner configured to determine at least one of the estimated brake temperature and the estimated landing distance according to user selection of the autobrake selection options.

IPC Classes  ?

  • B64C 19/00 - Aircraft control not otherwise provided for

22.

METHODS, SYSTEMS, AND HEADER STRUCTURES FOR TOOLING FIXTURE AND POST-CURE FIXTURE CALIBRATION

      
Document Number 03078032
Status Pending
Filing Date 2020-04-14
Open to Public Date 2020-10-15
Owner THE BOEING COMPANY (USA)
Inventor Borowicz, Clifford D.

Abstract

Systems and methods provide for the determination and correction of tooling deviation by comparing two different three-dimensional surface scans of a composite panel after curing. Such methods and systems may allow for less accurate post- cure fixturing (e.g., holding the panel in a less constrained state, as compared to prior art techniques), while still maintaining a sufficient amount of precision for predictive shimming and shimless techniques. Methods include performing a first three-dimensional surface scan, performing a second three-dimensional surface scan, and comparing the two to determine a deformation function corresponding to tooling deviation. In some systems, a header structure is used to hold the composite panel in a nominal configuration for the second three-dimensional surface scan. In some systems, scanning devices perform mirrored scanning on either side of the composite panel, using a common reference frame.

IPC Classes  ?

  • G01B 21/20 - Measuring arrangements or details thereof in so far as they are not adapted to particular types of measuring means of the other groups of this subclass for measuring contours or curvatures, e.g. determining profile
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • B64C 1/06 - Frames; Stringers; Longerons
  • G01S 17/89 - Lidar systems, specially adapted for specific applications for mapping or imaging

23.

POLYANILINES AND METHODS THEREOF

      
Document Number 03077487
Status Pending
Filing Date 2020-03-30
Open to Public Date 2020-10-10
Owner THE BOEING COMPANY (USA)
Inventor
  • Kinlen, Patrick J.
  • Flack, Matthew A.
  • Bruton, Eric A.

Abstract

The present disclosure provides polyanilines, articles thereof, and methods of forming polyanilines. In at least one aspect, a polyaniline has a thermal stability of about 100°C or greater, a weight average molecular weight (Mw) of from about 50,000 g/mol to about 150,000 g/mol and a molecular weight distribution (Mw/Mn) of from about 1 to about 5. In at least one aspect, a film includes a polyaniline, the film having a hydrocarbon content of about 1 wt% or less, based on the total weight of the film. In at least one aspect, a method includes introducing an emulsion of an aqueous solution of an aniline and an alkyl-substituted aryl sulfonic acid having 1 wt% or less of hydrocarbon content into a flow reactor, the flow reactor having a length of tubing having an inner diameter. The method includes polymerizing the monomer within the tube to form a polyaniline.

IPC Classes  ?

24.

MECHANICAL FASTENING SYSTEM AND ASSOCIATED STRUCTURAL ASSEMBLY AND METHOD

      
Document Number 03077814
Status Pending
Filing Date 2020-04-01
Open to Public Date 2020-10-02
Owner THE BOEING COMPANY (USA)
Inventor Chungbin, Jerry D.

Abstract

A structural assembly including a first structural member defining a first partial bore and including a first protrusion and a second protrusion, a second structural member defining a second partial bore and including a first protrusion and a second protrusion, wherein the second partial bore is aligned with the first partial bore to define a through- bore, a shaft extending through the through-bore, wherein the shaft includes a first end portion and a second end portion, a first engagement member proximate the first end portion, wherein the first engagement member engages both the first protrusion of the first structural member and the first protrusion of the second structural member, and a second engagement member proximate the second end portion, wherein the second engagement member engages both the second protrusion of the first structural member and the second protrusion of the second structural member.

IPC Classes  ?

  • F16B 35/00 - Screw-bolts; Stay bolts; Screw-threaded studs; Screws; Set screws
  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
  • F16B 1/00 - Devices for securing together, or preventing relative movement between, constructional elements or machine parts

25.

MULTIJUNCTION SOLAR CELL HAVING A FUSED SILICA COVER GLASS

      
Document Number 03075149
Status Pending
Filing Date 2020-03-11
Open to Public Date 2020-10-01
Owner THE BOEING COMPANY (USA)
Inventor
  • Rehder, Eric M.
  • Ho, Frank F.
  • Schwartz, Joel A.

Abstract

A solar cell includes a portion of a Germanium layer having a first side and a second side. The second side has properties consistent with a grinding and etching operation to thin a Germanium wafer to form the Germanium layer. Edges of the portion of the Germanium layer may have properties consistent with dicing using a diamond-coated saw. The portion of the Germanium layer may have a thickness of less than 150 micrometers. Compound semiconductor materials and circuitry are coupled to the first side of the portion of the Germanium layer to define a multijunction solar cell. A fused silica cover glass is coupled to the multijunction solar cell via a silicone-based adhesive.

IPC Classes  ?

  • H01L 31/18 - Processes or apparatus specially adapted for the manufacture or treatment of these devices or of parts thereof
  • H01L 31/0304 - Inorganic materials including, apart from doping materials or other impurities, only AIIIBV compounds

26.

FOLDABLE RAKED WING TIPS HAVING AERODYNAMIC DEVICES

      
Document Number 03069350
Status Pending
Filing Date 2020-01-22
Open to Public Date 2020-09-29
Owner THE BOEING COMPANY (USA)
Inventor
  • Dees, Paul W.
  • Detert, Bruce R.

Abstract

Foldable raked wing tips having aerodynamic devices are disclosed. A disclosed example wing for use with an aircraft includes a fixed portion, and a folding portion proximate a distal end of the wing. The folding portion includes a raked surface. The wing also includes at least one of a feather or a winglet, and a hinge operatively coupled between the fixed and folding portions to enable the folding portion to fold relative to the fixed portion.

IPC Classes  ?

  • B64C 3/56 - Folding or collapsing to reduce overall dimensions of aircraft
  • B64C 5/08 - Stabilising surfaces mounted on, or supported by, wings

27.

LAMINATED HYBRID METALLIZED POLYMER FILMS, SYSTEM, AND METHOD FOR EROSION PROTECTION OF COMPOSITE STRUCTURES

      
Document Number 03068679
Status Pending
Filing Date 2020-01-17
Open to Public Date 2020-09-26
Owner THE BOEING COMPANY (USA)
Inventor
  • Blohowiak, Kay Y.
  • Blohowiak, Denise A.
  • Kestner, James M.

Abstract

There is provided a laminated hybrid metallized polymer film for erosion protection of a composite structure. The laminated hybrid metallized polymer film includes a metal foil layer, a laminating adhesive layer underlying the metal foil layer, and a polymer film layer underlying the laminating adhesive layer. The polymer film layer is laminated to the metal foil layer with the laminating adhesive layer coupled between the metal foil layer and the polymer film layer. The laminated hybrid metallized polymer film further includes an adhesive layer underlying the polymer film layer. The adhesive layer adheres the polymer film layer to a substrate surface of the composite structure. The metal foil layer, the laminating adhesive layer, the polymer film layer, and the adhesive layer form the laminated hybrid metallized polymer film for application over and to the substrate surface of the composite structure.

IPC Classes  ?

  • B32B 7/12 - Interconnection of layers using interposed adhesives or interposed materials with bonding properties
  • C09J 7/22 - Plastics; Metallised plastics
  • B32B 15/08 - Layered products essentially comprising metal comprising metal as the main or only constituent of a layer, next to another layer of a specific substance of synthetic resin
  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like

28.

AUTOMATED FIBER-PLACEMENT SYSTEMS AND METHODS AND ARTICLES PRODUCED THEREFROM

      
Document Number 03068714
Status Pending
Filing Date 2020-01-17
Open to Public Date 2020-09-25
Owner THE BOEING COMPANY (USA)
Inventor
  • Johnson, Brice A.
  • Ghose, Sayata
  • Malik, Kevin F.

Abstract

An automated fiber-placement method (300) comprises delivering a first quantity of pulsed energy (122) to first discrete portions (124) of at least one fiber-reinforced tape strip (104), and delivering a second quantity of pulsed energy (123) to second discrete portions (125) of at least the one fiber-reinforced tape strip (104), alternating with the first discrete portions (124). The first quantity of pulsed energy (122) heats the first discrete portions (124) to a first temperature. The second quantity of pulsed energy (123) heats the second discrete portions (125) to a second temperature. The automated fiber-placement method (300) further comprises laying down at least the one fiber-reinforced tape strip (104) against a substrate (116) along a virtual curvilinear path (128), such that (i) at least the one fiber-reinforced tape strip (104) is centered on the virtual curvilinear path (128), and (ii) the first discrete portions (124) are transformed into discrete tape-regions (148), geometrically different from the first discrete portions (124).

IPC Classes  ?

  • B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns

29.

AUTONOMOUS DISTRESS TRACKING USING AUTOMATIC DEPENDENT SURVEILLANCE-BROADCAST

      
Document Number 03075238
Status Pending
Filing Date 2020-03-11
Open to Public Date 2020-09-22
Owner THE BOEING COMPANY (USA)
Inventor
  • Murphy, Timothy A.
  • Adler, Charles Otis
  • Turner Jessie

Abstract

A system and method for autonomous distress tracking of an aircraft. An automatic dependent surveillance-broadcast transceiver is configured to transmit an automatic distress transmission. A system controller comprises a distress identifier that is configured to determine when the aircraft is in a distress condition. The system controller is configured to control the automatic dependent surveillance-broadcast transceiver to transmit the automatic distress transmission in response to a determination that the aircraft is in the distress condition. The automatic dependent surveillance-broadcast transceiver and the system controller are contained within a housing attached to the aircraft on an outside of the aircraft.

IPC Classes  ?

  • G08G 5/00 - Traffic control systems for aircraft
  • H04W 84/02 - Hierarchically pre-organised networks, e.g. paging networks, cellular networks, WLAN [Wireless Local Area Network] or WLL [Wireless Local Loop]
  • H04W 88/06 - Terminal devices adapted for operation in multiple networks, e.g. multi-mode terminals
  • B64D 25/00 - Emergency apparatus or devices, not otherwise provided for
  • B64D 47/06 - Arrangements or adaptations of signal or lighting devices for indicating aircraft presence
  • H04B 1/40 - Circuits
  • H04B 7/26 - Radio transmission systems, i.e. using radiation field for communication between two or more posts at least one of which is mobile
  • G01S 1/00 - Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith

30.

COMPRESSED AIR SYSTEM

      
Document Number 03069702
Status Pending
Filing Date 2020-01-23
Open to Public Date 2020-09-20
Owner THE BOEING COMPANY (USA)
Inventor
  • Atkey, Warren A.
  • Mackin, Steve G.
  • Boggs, Royal E.
  • El-Gabalawy, Hosam E.

Abstract

A method for controlling compressed air sent to pneumatic systems. The method includes acquiring a set of performance demands for each of a plurality of pneumatic systems in a platform, where the performance demands indicate needs for the compressed air supplied to each of the pneumatic systems, identifying a maximum allowable air discharge temperature limit of a variable speed air compressor configured to supply compressed air to the pneumatic systems, and controlling an operation of the compressor to supply the compressed air to the pneumatic systems to meet the acquired performance demands for at least one of the pneumatic systems while operating the compressor below the maximum allowable air discharge temperature limit.

IPC Classes  ?

  • F04B 49/20 - Control of, or safety measures for, machines, pumps, or pumping installations, not otherwise provided for in, or of interest apart from, groups by changing the driving speed
  • B64D 13/02 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space the air being pressurised
  • B64D 15/02 - De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
  • B64D 41/00 - Power installations for auxiliary purposes
  • B64D 47/00 - Equipment not otherwise provided for
  • F04B 49/22 - Control of, or safety measures for, machines, pumps, or pumping installations, not otherwise provided for in, or of interest apart from, groups by means of valves
  • F15B 21/04 - Special measures taken in connection with the properties of the fluid

31.

SUB-SURFACE PATTERNING FOR DIFFRACTION-BASED STRAIN MEASUREMENT AND DAMAGE DETECTION IN STRUCTURES

      
Document Number 03072799
Status Pending
Filing Date 2020-02-18
Open to Public Date 2020-09-14
Owner THE BOEING COMPANY (USA)
Inventor
  • Georgeson, Gary E.
  • Griess, Kenneth H.
  • Keller, Russell L.

Abstract

Systems and methods for assessing strain in structural components are disclosed. Structural components may have geometric patterns of grooves within the structural component, with the grooves in the geometric pattern each having a groove width. The method may include projecting beams of electromagnetic (EM) energy through the structural component to the geometric pattern of grooves to create diffracted beams of EM energy that are reflected from or transmitted through the geometric pattern of grooves and have diffracted wavelengths indicating changes in the groove widths due to strain caused when the structural component is exposed to environmental conditions, detecting the diffracted wavelength of the diffracted beams, and correlating the diffracted wavelengths of the diffracted beams to the strain in the structural components.

IPC Classes  ?

  • G01B 11/16 - Measuring arrangements characterised by the use of optical means for measuring the deformation in a solid, e.g. optical strain gauge
  • B32B 7/023 - Optical properties
  • B32B 3/30 - Layered products essentially comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar form; Layered products essentially having particular features of form characterised by a layer with cavities or internal voids characterised by a layer formed with recesses or projections, e.g. grooved, ribbed
  • B32B 15/00 - Layered products essentially comprising metal

32.

OPERATIONAL FLIGHT ENVELOPE MANAGEMENT SYSTEM

      
Document Number 03072802
Status Pending
Filing Date 2020-02-18
Open to Public Date 2020-09-14
Owner THE BOEING COMPANY (USA)
Inventor Leopold, David Daniel

Abstract

A method, apparatus, and system for adjusting an operational flight envelope for an aircraft. An airspeed of the aircraft is received from a sensor system in the aircraft. An amount of change in the airspeed of the aircraft is determined. A current ceiling of the operational flight envelope for the aircraft is adjusted based on the amount of change in the airspeed of the aircraft.

IPC Classes  ?

  • G01C 21/20 - Instruments for performing navigational calculations
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • G05D 1/10 - Simultaneous control of position or course in three dimensions

33.

AUXILIARY POWER UNIT ENCLOSURE AND METHOD OF MAKING THE SAME

      
Document Number 03074359
Status Pending
Filing Date 2020-03-02
Open to Public Date 2020-09-08
Owner THE BOEING COMPANY (USA)
Inventor
  • Pearson, Steven E.
  • Vingiani, Rosario
  • Margessery, Rajagopalan
  • Dopker, Bernhard
  • Rosman, Richard R.

Abstract

An auxiliary power unit enclosure of an aircraft includes a space frame configured to carry a load and defining an auxiliary power unit compartment. The space frame includes a plurality of frame elements coupled together at a plurality of nodes. The auxiliary power unit enclosure also includes a fairing coupled to and surrounding the space frame.

IPC Classes  ?

  • B64C 7/00 - Structures or fairings not otherwise provided for
  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
  • B64D 41/00 - Power installations for auxiliary purposes

34.

MULTI-ROTOR VEHICLE WITH EDGE COMPUTING SYSTEMS

      
Document Number 03074358
Status Pending
Filing Date 2020-03-02
Open to Public Date 2020-09-06
Owner THE BOEING COMPANY (USA)
Inventor
  • Dong, John Jian
  • Duffy, Michael James
  • Cameron, Doughlas C.
  • Hussain, Naveed Moayyed

Abstract

A multi-rotor vehicle includes a plurality of electric motors and edge computing systems (ECSs). The electric motors are operatively coupled to respective rotors, and cause the respective rotors to rotate relative to the airframe. The ECSs are independent, distinct and distributed to the electric motors, each operatively coupled to a respective electric motor and thereby a respective rotor. Each ECS is configured to acquire and process sensor data for the respective rotor to determine rotor status information, and execute motor commands to control the respective electric motor and thereby the respective rotor. The ECSs are configured according to a model in which any of the ECSs is selectable as a primary ECS, and others of the ECSs are operable as secondary ECSs, the secondary ECSs configured to communicate respective rotor status information to the primary ECS, and the primary ECS configured to provide the motor commands to the secondary ECSs.

IPC Classes  ?

  • B64C 27/08 - Helicopters with two or more rotors
  • B64C 39/02 - Aircraft not otherwise provided for characterised by special use
  • B64D 27/24 - Aircraft characterised by the type or position of power plant using steam, electricity, or spring force
  • B64D 31/00 - Power plant control; Arrangement thereof
  • G05B 19/042 - Programme control other than numerical control, i.e. in sequence controllers or logic controllers using digital processors
  • H02P 5/46 - Arrangements specially adapted for regulating or controlling the speed or torque of two or more electric motors for speed regulation of two or more dynamo-electric motors in relation to one another

35.

TOOL ORIENTATION SYSTEMS AND METHODS

      
Document Number 03074361
Status Pending
Filing Date 2020-03-02
Open to Public Date 2020-09-06
Owner THE BOEING COMPANY (USA)
Inventor
  • Thompson, Brian Arthur
  • Davis, Jonathan T.

Abstract

Systems and methods for tool orientation and/or position determining system are described herein. In one example, a plurality of tool sensors can be coupled to a tool. The tool sensors can provide data to a control module or system controller. The orientation and/or position of the tool can accordingly be determined from the data. If the orientation and/or position of the tool matches a desired orientation, the tool and/or control module can provide an indication that the tool is in the desired orientation.

IPC Classes  ?

  • B23Q 17/22 - Arrangements for indicating or measuring on machine tools for indicating or measuring existing or desired position of tool or work
  • B23B 45/14 - Means for holding or guiding the drilling device or for securing it to the work; Thrust stands

36.

AUTOMATIC CALIBRATION FOR A ROBOT OPTICAL SENSOR

      
Document Number 03067515
Status Pending
Filing Date 2020-01-10
Open to Public Date 2020-09-05
Owner THE BOEING COMPANY (USA)
Inventor
  • Haeusler, Phillip
  • Cochrane, Jason John

Abstract

Systems and methods are provided for automatic intrinsic and extrinsic calibration for a robot optical sensor. An implementation includes an optical sensor; a robot arm; a calibration chart; one or more processors; and a memory storing instructions that cause the one or more processors to perform operations that includes: determining a set of poses for calibrating the first optical sensor; generating, based at least on the set of poses, pose data comprising three dimensional (3D) position and orientation data; moving, based at least on the pose data, the robot arm into a plurality of poses; at each pose of the plurality of poses, capturing a set of images of the calibration chart with the first optical sensor and recording a pose; calculating intrinsic calibration parameters, based at least on the set of captured images; and calculating extrinsic calibration parameters, based at least on the set of captured images.

IPC Classes  ?

  • G01J 1/02 - Photometry, e.g. photographic exposure meter - Details
  • B25J 19/02 - Sensing devices

37.

THERMOGRAPHIC INSPECTION FOR TAPE LAYUP MACHINES

      
Document Number 03074093
Status Pending
Filing Date 2020-02-26
Open to Public Date 2020-09-04
Owner THE BOEING COMPANY (USA)
Inventor
  • Holmes, Tyler
  • Hansen, Amanda
  • Brady, Steven K.

Abstract

Systems and methods are provided for thermal inspection of tape layup. One embodiment is a method for performing inspection of a tape layup. The method comprises laying up tape onto a surface of a laminate, applying heat to tack the tape to the surface, and generating thermographic images of the tape as applied to the surface.

IPC Classes  ?

  • B29C 64/147 - Processes of additive manufacturing using only solid materials using sheet material, e.g. laminated object manufacturing [LOM] or laminating sheet material precut to local cross sections of the 3D object
  • B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

38.

METHODS AND DEVICES FOR MACHINING A CHILLED WORKPIECE

      
Document Number 03073764
Status Pending
Filing Date 2020-02-25
Open to Public Date 2020-08-28
Owner THE BOEING COMPANY (USA)
Inventor Borowicz, Clifford D.

Abstract

Machining apparatus for machining a chilled workpiece include a support surface that supports the chilled workpiece during machining by a machining tool of the machining apparatus, and further include a cooling system operatively coupled to the support surface. The cooling system prevents a machining temperature of an adhesive coupled to the chilled workpiece from rising beyond a predetermined threshold temperature during machining of the chilled workpiece, such that the cooling system prevents curing of the adhesive during machining of the chilled workpiece. The cooling system includes a cooling fluid that radiantly cools the chilled workpiece via the support surface while the chilled workpiece is supported by the support surface, such that the cooling system maintains the machining temperature of the adhesive (and of the chilled workpiece) below an ambient temperature. Related methods include machining the chilled workpiece using such machining apparatus.

IPC Classes  ?

  • B23Q 11/12 - Arrangements for cooling or lubricating parts of the machine
  • B23Q 11/10 - Arrangements for cooling or lubricating tools or work

39.

PLUG GAUGE AND ASSCOCIATED SYSTEM AND METHOD FOR TAKING MULTIPLE SIMULTANEOUS DIAMETRIC MEASUREMENTS

      
Document Number 03074083
Status Pending
Filing Date 2020-02-26
Open to Public Date 2020-08-27
Owner THE BOEING COMPANY (USA)
Inventor
  • Albrecht, Mark
  • Chan, Kwok Tung
  • Sisco, Tanni
  • Gray, Everette D.

Abstract

A plug gauge includes a housing, defining an internal volume, first openings, and second openings. The plug gauge includes first contact elements, each at least partially received in a respective one of the first openings. The plug gauge includes a first plunger in the internal volume and movable relative to the housing. The first plunger is biased to urge the first contact elements radially outward through the first openings. The plug gauge includes a first sensor sensing movement of the first plunger. The plug gauge includes second contact elements, each at least partially received in a respective one of the second openings. The plug gauge includes a second plunger in the internal volume and movable relative to the housing. The second plunger is biased to urge the second contact elements radially outward through the second openings. The plug gauge includes a second sensor sensing movement of the second plunger.

IPC Classes  ?

  • G01B 5/12 - Measuring arrangements characterised by the use of mechanical means for measuring diameters internal diameters

40.

BULKHEAD SHIMS FOR CURVILINEAR COMPONENTS

      
Document Number 03065464
Status Pending
Filing Date 2019-12-18
Open to Public Date 2020-08-26
Owner THE BOEING COMPANY (USA)
Inventor
  • Stark, Rich L.
  • Lakic, Branko
  • Pasik, Jared Marvin
  • Williams, Daniel D.

Abstract

A method of assembling thin-walled curvilinear components to a bulkhead offers a cost-effective, time-saving process of manufacture. Each component includes a faying edge configured to be aligned with respect to the other. A first component and the bulkhead are preassembled. In one approach, a second component is clamped about the bulkhead for a preassembly measurement of radial gaps between the faying edge of the second component and the bulkhead. An average value of the radial gaps is calculated, and a specific shim thickness corresponding to the calculated average gap value is selected. The second component is unclamped, and a plurality of shims, each having the selected thickness corresponding to the calculated average gap value, is applied about the bulkhead. The second component is then permanently secured to the bulkhead over the shims, with respective faying edges of the first and second components fixed in radial alignment with each other.

IPC Classes  ?

  • B23P 19/10 - Aligning parts to be fitted together
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
  • B64C 1/12 - Construction or attachment of skin panels
  • B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
  • B64D 29/00 - Power-plant nacelles, fairings, or cowlings

41.

SYSTEMS AND METHODS FOR TAIL-SPECIFIC PARAMETER COMPUTATION

      
Document Number 03067151
Status Pending
Filing Date 2020-01-07
Open to Public Date 2020-08-25
Owner THE BOEING COMPANY (USA)
Inventor
  • Root, Robert Edwin
  • Kaul, Charles E.
  • Tylee, James Louis

Abstract

A device for tail-specific parameter computation includes a memory, a network interface, and a processor. The memory is configured to store a tail-specific aircraft performance model for a first aircraft of an aircraft type. The tail-specific aircraft performance model is based on historical flight data of the first aircraft and a nominal aircraft performance model associated with a second aircraft of the aircraft type. The network interface is configured to receive flight data from a databus of the first aircraft. The processor is configured to generate, based at least in part on the flight data and the tail-specific aircraft performance model, a recommended cost index and a recommended cruise altitude. The processor is also configured to provide the recommended cost index and the recommended cruise altitude to a display device.

IPC Classes  ?

  • G06Q 10/00 - Administration; Management
  • G07C 5/08 - Registering or indicating performance data other than driving, working, idle, or waiting time, with or without registering driving, working, idle, or waiting time

42.

SYSTEMS AND METHODS FOR LAUNCHING A PLURALITY OF SPACECRAFT

      
Document Number 03060150
Status Pending
Filing Date 2019-10-25
Open to Public Date 2020-08-22
Owner THE BOEING COMPANY (USA)
Inventor
  • Mansour, Sadek W.
  • Lemke, Gary E.
  • Flathom, Jason D.
  • Noel, Jeffrey S.

Abstract

Systems and methods for launching a plurality of spacecraft, provided in a stack of spacecraft, from a launch vehicle traveling along an in-track path include releasing, in a first separation event occurring at a first time, a first spacecraft from the stack of spacecraft using a first separation force having a first separation force in-track component along the in-track path. Subsequently, in a second separation event occurring at a second time, a second spacecraft is released from the stack of spacecraft using a second separation force having a second separation force in-track component along the in-track path, wherein the second time occurs a first time delay after the first time. The first and second separation in-track components may be different, such as by varying a magnitude of the separation force or an angle at which the spacecraft is launched.

IPC Classes  ?

  • B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
  • B64G 1/10 - Artificial satellites; Systems of such satellites; Interplanetary vehicles

43.

ROBOTIC LASER AND VACUUM CLEANING FOR ENVIRONMENTAL GAINS

      
Document Number 03065858
Status Pending
Filing Date 2019-12-19
Open to Public Date 2020-08-11
Owner THE BOEING COMPANY (USA)
Inventor
  • Bolton, Joseph Andrew
  • Humfeld, Keith Daniel

Abstract

Methods, systems, and apparatuses are disclosed for the selective and controlled removal of debris from specific areas of a substrate outer surface without adversely impacting the substrate outer surface, including substrate outer surface coatings, and returning an actual substrate outer surface profile containing affixed debris to a predetermined substrate outer surface profile by comparing a library of predetermined profiles to an actual substrate outer surface profile in real time.

IPC Classes  ?

  • B08B 5/00 - Cleaning by methods involving the use of air flow or gas flow
  • G01N 21/94 - Investigating contamination, e.g. dust
  • G01N 37/00 - INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES - Details not covered by any other group of this subclass

44.

APPARATUS AND METHOD TO TAILOR FIBER DISTORTION IN COMPOSITE PARTS

      
Document Number 03064841
Status Pending
Filing Date 2019-12-10
Open to Public Date 2020-08-07
Owner THE BOEING COMPANY (USA)
Inventor Saini, Gagandeep

Abstract

A caul plate for application onto an uncured composite material which includes a first slit defined by and which extends through and along the caul plate. Further included is a method for curing a composite material part having geometric change within the part. The method includes fabricating a part constructed from uncured composite material having a geometric change within the uncured composite material, which includes a step of positioning a caul plate in overlying relationship to the uncured composite material having a geometric change in the uncured composite material, wherein the caul plate includes a first slit defined by and which extends through and along the caul plate.

IPC Classes  ?

  • B29C 70/36 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and impregnating by casting, e.g. vacuum casting

45.

FOLDABLE AIRCRAFT WINGS

      
Document Number 03062006
Status Pending
Filing Date 2019-11-18
Open to Public Date 2020-08-01
Owner THE BOEING COMPANY (USA)
Inventor
  • Dees, Paul W.
  • Gruner, Eric
  • Addington, Michael
  • Boes, David Douglas
  • Blohm, Eric Dwight
  • Elenbaas, Matthew Scott
  • Hansken, Rickie
  • Herzberg, Mark John
  • Kamila, Eric Sean
  • Olds, Jeffrey Michael
  • Soman, Charuhas
  • Townsend, Keith
  • Walker, Steven Paul

Abstract

Foldable aircraft wings are disclosed. An example aircraft includes a foldable wing having a fixed wing portion, a foldable wing portion and a hinge to pivotally couple the foldable wing portion relative to the fixed wing portion. The hinge includes a wing transition portion including wing hinge ribs and wing stub ribs, respective ones of the wing hinge ribs coupled to corresponding respective ones of the wing stub ribs. The hinge also includes a tip transition portion including tip hinge ribs, where respective ends of the tip hinge ribs positioned between corresponding respective ones of the wing hinge ribs and the wing stub ribs.

IPC Classes  ?

  • B64C 3/56 - Folding or collapsing to reduce overall dimensions of aircraft
  • F16C 11/04 - Pivotal connections

46.

TAMPER RESISTANT COUNTERS

      
Document Number 03070702
Status Pending
Filing Date 2020-01-30
Open to Public Date 2020-07-31
Owner THE BOEING COMPANY (USA)
Inventor Hars, Laszlo

Abstract

A method of persistently storing event counts includes generating, using a secret cryptographic key, a sequence of numbers arranged in a pseudorandom order. The sequence of numbers is indicative of a sequence of addresses of cells in an array of cells. Each cell in the array of cells is programmable from an initial state to a programmed state to persistently encode data indicative of counter values associated with a particular event. The method also includes comparing addresses of cells having the programmed state with the sequence of addresses to determine whether a tampering event occurred at the array of cells. The method further includes, based on the determination, authenticating the array of cells or performing a countermeasure.

IPC Classes  ?

  • G06F 21/55 - Detecting local intrusion or implementing counter-measures
  • G06F 21/44 - Program or device authentication
  • G06F 21/78 - Protecting specific internal or peripheral components, in which the protection of a component leads to protection of the entire computer to assure secure storage of data

47.

FOUR-DIMENSIONAL TRAJECTORY UPLINKING SYSTEM FOR AIRCRAFT

      
Document Number 03069393
Status Pending
Filing Date 2020-01-22
Open to Public Date 2020-07-30
Owner THE BOEING COMPANY (USA)
Inventor
  • Ayhan, Samet M.
  • Wilson, Ian A.

IPC Classes  ?

  • G08G 5/00 - Traffic control systems for aircraft
  • H04W 4/12 - Messaging; Mailboxes; Announcements
  • B64D 47/00 - Equipment not otherwise provided for
  • G05D 1/10 - Simultaneous control of position or course in three dimensions
  • H04L 12/58 - Message switching systems

48.

AIRCRAFT AUXILIARY POWER UNIT (APU) CONTROL SYSTEM HAVING SPEED COMPENSATION

      
Document Number 03068669
Status Pending
Filing Date 2020-01-17
Open to Public Date 2020-07-29
Owner THE BOEING COMPANY (USA)
Inventor White, Jeffrey J.

Abstract

An auxiliary power unit (APU) control system for an aircraft is disclosed, and includes an APU drivingly coupled to one or more generators, one or more processors, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the APU control system to receive one or more ambient signals indicative of an air density value and one or more power signals indicative of a specific amount of power generated by the APU. The system is further caused to determine a first variable rotational speed of the APU based on the air density value. The APU continues to generate the specific amount of power when operating at the first variable rotational speed. After instructing the APU to operate at the first variable rotational speed, the system receives an electrical load signal.

IPC Classes  ?

  • B64D 41/00 - Power installations for auxiliary purposes
  • B64D 31/00 - Power plant control; Arrangement thereof
  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • F02C 9/00 - Controlling gas-turbine plants; Controlling fuel supply in air-breathing jet-propulsion plants

49.

AIRCRAFT AUXILIARY POWER UNIT(APU) CONTROL SYSTEM HAVING SPEED COMPENSATION

      
Document Number 03068665
Status Pending
Filing Date 2020-01-17
Open to Public Date 2020-07-29
Owner THE BOEING COMPANY (USA)
Inventor White, Jeffrey J.

Abstract

An auxiliary power unit (APU) control system for an aircraft is disclosed. The APU control system includes an APU, one or more processors, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the APU control system to receive a one or more ambient signals indicative of an air density value and one or more power signals indicative of a specific amount of power generated by the APU. The APU control system is further caused to determine a variable rotational speed of the APU based on the air density value and instruct the APU to operate at the variable rotational speed. The APU continues to generate the specific amount of power when operating at the variable rotational speed.

IPC Classes  ?

  • B64D 41/00 - Power installations for auxiliary purposes
  • B64D 31/00 - Power plant control; Arrangement thereof
  • F01D 15/10 - Adaptations for driving, or combinations with, electric generators
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • F02C 9/00 - Controlling gas-turbine plants; Controlling fuel supply in air-breathing jet-propulsion plants

50.

APPLICATION OF ARTIFICIAL INTELLIGENCE TO IMPLEMENT AUGMENTED REALITY, VIRTUAL REALITY, AND MIXED REALITY TO ENHANCE PASSENGER EXPERIENCE TO FLYING WITH MOOD LIGHTING

      
Document Number 03060296
Status Pending
Filing Date 2019-10-25
Open to Public Date 2020-07-21
Owner THE BOEING COMPANY (USA)
Inventor
  • Madhav, Jagdish T.
  • Colwell, Barry C.

Abstract

An aircraft includes a fuselage and a cabin area with a plurality of windows. The aircraft includes a plurality of projectors positioned within the cabin area that are oriented toward corresponding windows. The projectors project an image over the glass portion of the corresponding window and surrounding surfaces. The image includes a dark center region that is aligned with the glass portion of the corresponding window, reducing undesired effect on passengers. The dark center region may reduce a reflective glare from the glass portion of the corresponding window. The image may include an outer region around the dark center region, which may be brighter than the dark center region. The outer region may illuminate a window bezel and/or a portion of a cabin sidewall. The aircraft may include a plurality of cameras positioned to acquire an outside image that may be added to the image projected by the projectors.

IPC Classes  ?

  • B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for
  • B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
  • G09F 19/18 - Advertising or display means not otherwise provided for using special optical effects involving the use of optical projection means, e.g. projection of images on clouds

51.

AIRCRAFT MAINTENANCE SYSTEMS AND METHODS

      
Document Number 03060153
Status Pending
Filing Date 2019-10-24
Open to Public Date 2020-07-18
Owner THE BOEING COMPANY (USA)
Inventor
  • Best, Timothy A.
  • Pierre, Ravin R.
  • Nikjou, Hamid R.

IPC Classes  ?

  • B64D 47/00 - Equipment not otherwise provided for

52.

AIRCRAFT DOOR HINGE ROTATION

      
Document Number 03064052
Status Pending
Filing Date 2019-12-05
Open to Public Date 2020-07-14
Owner THE BOEING COMPANY (USA)
Inventor Jackson, Rick A.

Abstract

An aircraft including a fuselage, an aircraft fuselage end cargo door, and a fuselage end cargo door mechanism. The aircraft fuselage end cargo door couples to the fuselage at a major joint line. The fuselage end cargo door mechanism including a hinge rotatably coupling an aircraft fuselage end cargo door to a fuselage, the hinge being coupled to both the aircraft fuselage end cargo door and the fuselage so that an axis of rotation of the aircraft fuselage end cargo door, defined by the hinge, relative to the fuselage is located forward of a major joint line between the aircraft fuselage end cargo door and the fuselage, wherein an uppermost portion of the major joint line comprises a joint line radius where a portion of the joint line radius formed by the aircraft fuselage end cargo door pivots within another portion of the joint line radius formed by the fuselage.

IPC Classes  ?

  • B64C 1/14 - Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens
  • B64C 1/22 - Other structures integral with fuselages to facilitate loading

53.

AIRCRAFT WING COMPOSITE RIBS HAVING ELECTRICAL GROUNDING PATHS

      
Document Number 03067469
Status Pending
Filing Date 2020-01-09
Open to Public Date 2020-07-14
Owner THE BOEING COMPANY (USA)
Inventor Walker, Steven Paul

Abstract

Aircraft wing composite ribs having electrical grounding paths are described. An example composite rib includes a carbon fiber reinforced plastic (CFRP) panel, a metallic rib post, a metallic fitting, and a metallic grounding member. The metallic rib post is coupled to the CFRP panel and configured to be coupled to a spar of an aircraft wing, the spar being coupled to a current return network (CRN) cable. The metallic fitting is coupled to the CFRP panel and configured to be coupled to a skin panel of the aircraft wing. The metallic grounding member is positioned between the CFRP panel and the metallic fitting. The metallic grounding member provides an electrical grounding path extending from the metallic fitting to the metallic rib post.

IPC Classes  ?

  • B64C 3/18 - Spars; Ribs; Stringers
  • B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels
  • B64D 45/02 - Lightning protectors; Static dischargers
  • F16B 5/02 - Joining sheets or plates to one another or to strips or bars parallel to them by means of fastening members using screw-thread

54.

AIRCRAFT CARGO FLOOR ARCHITECTURE AND METHOD OF MODIFYING THE AIRCRAFT CARGO FLOOR ARCHITECTURE

      
Document Number 03054438
Status Pending
Filing Date 2019-09-04
Open to Public Date 2020-07-11
Owner THE BOEING COMPANY (Canada)
Inventor
  • Spry, Michael D.
  • Ulvin, Mark A.

Abstract

An aircraft cargo floor architecture comprises a plurality of aircraft keel frames. One or more longitudinal rails are attached directly to the aircraft keel frames. The one or more longitudinal rails are designed to provide structural support for an aircraft cargo floor.

IPC Classes  ?

  • B64C 1/20 - Floors specially adapted for freight

55.

RECOGNITION FEATURES FOR A CONSUMABLE ARTICLE

      
Document Number 03063074
Status Pending
Filing Date 2019-11-27
Open to Public Date 2020-07-09
Owner THE BOEING COMPANY (Canada)
Inventor Mcintosh, Darren Carl

Abstract

Methods, systems, and apparatuses are disclosed for providing physical validation of for precluding improper installation and confirming appropriate installation of a consumable articles into a consumable article dispenser, and further monitoring the appropriate installation and consumption of a consumable article in real- time.

IPC Classes  ?

  • A47K 10/16 - Paper towels; Toilet paper; Holders therefor
  • A47K 10/34 - Dispensers for paper towels or toilet-paper dispensing from a web, e.g. with mechanical dispensing means
  • B65H 26/06 - Warning or safety devices, e.g. automatic fault detectors, stop-motions, for web-advancing mechanisms responsive to predetermined lengths of webs
  • B65H 43/00 - Use of control, checking, or safety devices, e.g. automatic devices comprising an element for sensing a variable
  • B65H 75/02 - Cores, formers, supports, or holders for coiled, wound, or folded material, e.g. reels, spindles, bobbins, cop tubes, cans
  • G01S 1/00 - Beacons or beacon systems transmitting signals having a characteristic or characteristics capable of being detected by non-directional receivers and defining directions, positions, or position lines fixed relatively to the beacon transmitters; Receivers co-operating therewith
  • G06K 19/07 - Record carriers with conductive marks, printed circuits or semiconductor circuit elements, e.g. credit or identity cards with integrated circuit chips

56.

STRUCTURAL JOINT OF TWO LOAD CARRYING WALLS OF A PRESSURIZED VESSEL

      
Document Number 03062115
Status Pending
Filing Date 2019-11-19
Open to Public Date 2020-07-08
Owner THE BOEING COMPANY (Canada)
Inventor
  • Sidiropoulos, Aristidis
  • Keith, William P.

Abstract

Disclosed herein is a structure that comprises a tank including an outer cylindrical surface and a domed end. The structure also comprises a tank skirt positioned circumferentially around the tank. A wall of the tank and a wall of the tank skirt form two sides of a y-joint between the tank and the tank skirt. The y- joint includes a wedge structure positioned between the tank and the tank skirt. Additionally, a thickness of at least one of the wall of the tank or the wall of the tank skirt forming the y-joint tapers such that the thickness of the at least one of the wall of the tank or the wall of the tank skirt that tapers has a greater thickness at the y-joint than away from the y-joint.

IPC Classes  ?

  • F17C 13/00 - VESSELS FOR CONTAINING OR STORING COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES; FIXED-CAPACITY GAS-HOLDERS; FILLING VESSELS WITH, OR DISCHARGING FROM VESSELS, COMPRESSED, LIQUEFIED, OR SOLIDIFIED GASES - Details of vessels or of the filling or discharging of vessels
  • B64G 1/22 - Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
  • F17C 1/00 - Pressure vessels, e.g. gas cylinder, gas tank, replaceable cartridge

57.

TITANIUM-BASED COATINGS AND METHODS FOR MAKING COATINGS

      
Document Number 03064839
Status Pending
Filing Date 2019-12-10
Open to Public Date 2020-07-03
Owner THE BOEING COMPANY (Canada)
Inventor
  • Vajo, John J.
  • Adjorlolo, Alain A.
  • Graetz, Jason

Abstract

Aspects of the present disclosure provide titanium-based coatings and methods for making titanium-based coatings on surfaces. In at least one aspect, a coating includes an oxygen content, a fluorine content, a titanium content, and a sodium content. In one or more additional aspects, a coating includes titanium dioxide and Na5Ti3F14. In one or more additional aspects, a method of making a titanium- based coating includes contacting a substrate with a composition that includes from about 0.01 M to about 0.8 M of a titanium fluoride, from about 0.01 M to about 2 M of a sodium salt, and from about 0.1 M to about 1.5 M of a fluorine scavenger.

IPC Classes  ?

  • C23C 30/00 - Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
  • C23C 18/54 - Contact plating, i.e. electroless electrochemical plating

58.

EME PROTECTION CAP SYSTEM WITH SCREW SEALANT MECHANISM

      
Document Number 03063667
Status Pending
Filing Date 2019-12-03
Open to Public Date 2020-07-03
Owner THE BOEING COMPANY (Canada)
Inventor
  • Auffinger, Sean
  • Stevens, Bart

Abstract

A containment cap assembly for enclosing a metallic fastener extending through a structure includes an inner cap with a projection extending from an outer surface of the inner cap and an outer cap includes a first end which defines an opening and includes an inner surface which defines a first space within the outer cap in communication with the opening. A dimension of the opening and of the first space defined by the inner surface of the outer cap are each greater than a dimension defined by the outer surface of the inner cap such that with positioning the inner cap within the outer cap, a second space is defined between the outer cap and the inner cap. A slot of the outer cap extends first curvilinear direction such that the projection positioned within the slot moves along first curvilinear direction with moving the inner cap into the outer cap.

IPC Classes  ?

59.

MULTI-EMBEDDED RADIO FREQUENCY BOARD AND MOBILE DEVICE INCLUDING THE SAME

      
Document Number 03059703
Status Pending
Filing Date 2019-10-23
Open to Public Date 2020-07-02
Owner THE BOEING COMPANY (Canada)
Inventor
  • Wu, Shihchang
  • Woolrich, Kyle A.
  • Spence, Jay Stuart

Abstract

A multi-embedded radio frequency board includes a plurality of printed circuit boards stacked one on the others, at least one of the printed circuit boards of the plurality of printed circuit boards being configured so as to have a different processing function than another processing function of another printed circuit board of the plurality of printed circuit boards, and an interconnection join layer disposed between adjacent printed circuit boards of the plurality of printed circuit boards so as to physically and electrically couple the adjacent printed circuit boards to each other so as to form an integrated printed circuit board module having a predetermined radio frequency communication characteristic.

IPC Classes  ?

60.

AUGMENTED REALITY SYSTEM USING ENHANCED MODELS

      
Document Number 03059940
Status Pending
Filing Date 2019-10-24
Open to Public Date 2020-07-02
Owner THE BOEING COMPANY (USA)
Inventor
  • Kelsey, William David
  • Laughlin, Brian Dale

Abstract

A method, apparatus, and system for visualizing information. An augmented reality system comprises a computer system and a visualizer in the computer system. The computer system is in communication with unmanned vehicles using communications links. The visualizer system receives images of a physical object from the unmanned vehicles moving relative to the physical object and receive scan data for a region of the physical object from the unmanned vehicles. The visualizer creates an enhanced model of the physical object using the images and the scan data. The region of the physical object in the enhanced model has a greater amount of detail than the other regions of the physical object. The visualizer sends information to a portable computing device that is displayable by the portable computing device on a live view of the physical object. The information is identified using the enhanced model of the physical object.

IPC Classes  ?

  • H04N 19/167 - Position within a video image, e.g. region of interest [ROI]
  • G06T 19/00 - Manipulating 3D models or images for computer graphics
  • G06K 9/00 - Methods or arrangements for reading or recognising printed or written characters or for recognising patterns, e.g. fingerprints
  • G06T 17/00 - 3D modelling for computer graphics
  • H04N 7/18 - Closed-circuit television systems, i.e. systems in which the signal is not broadcast

61.

COMPOSITE PART RESIN INFUSION WITH DYNAMIC THICKNESS CONTROL

      
Document Number 03065009
Status Pending
Filing Date 2019-12-13
Open to Public Date 2020-07-02
Owner THE BOEING COMPANY (Canada)
Inventor
  • Meure, Samuel James
  • Cuckson, Ian
  • Orr, Jessica Claire
  • Howe, Christopher

Abstract

Systems and methods are provided for fabricating composite parts. One embodiment is a method of fabricating a composite part. The method includes providing a preform on a tool mandrel, positioning sensors around the preform according to a target shape of the composite part, and sealing the preform with a vacuum bag to form a chamber. The method also includes applying temperature and pressure to the chamber to infuse a resin into the preform to create a composite preform undergoing infusion, monitoring a thickness of the composite preform prior to completing cure, and adjusting at least one of the temperature and the pressure prior to completing cure based on the thickness.

IPC Classes  ?

  • B29C 70/36 - Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and impregnating by casting, e.g. vacuum casting

62.

COORDINATING WORK WITHIN A MULTI-ROBOT CELL

      
Document Number 03059906
Status Pending
Filing Date 2019-10-24
Open to Public Date 2020-07-02
Owner THE BOEING COMPANY (Canada)
Inventor Pedigo, Samuel F.

Abstract

Systems and methods are provided for robot control. One embodiment is a method for coordinating operations of robots performing work on a part. The method includes assigning a goup of robots to a part, initiating work on the part via the group of robots, determining that a robot within the group is unable to continue performing work at a first location of the part, removing the robot from the group while other robots of the group continue performing the work, adding a functioning robot to the group at a second location that the robot is scheduled to occupy, and continuing work on the part via the group of robots.

IPC Classes  ?

  • B25J 9/18 - Programme controls electric
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
  • B23Q 39/04 - Metal-working machines incorporating a plurality of sub-assemblies, each capable of performing a metal-working operation the sub-assemblies being arranged to operate simultaneously at different stations, e.g. with an annular work-table moved in steps
  • B23Q 41/06 - Features relating to organisation of working of machines
  • G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control (DNC), flexible manufacturing systems (FMS), integrated manufacturing systems (IMS), computer integrated manufacturing (CIM)

63.

NON-DESTRUCTIVE INSPECTION USING UNMANNED AERIAL VEHICLE

      
Document Number 03063386
Status Pending
Filing Date 2019-11-29
Open to Public Date 2020-07-02
Owner THE BOEING COMPANY (Canada)
Inventor
  • Troy, James J.
  • Georgeson, Gary E.
  • Hafenrichter, Joseph L.
  • Lea, Scott W.

Abstract

Provided is a nondestructive inspection ("NDI") system that includes an unmanned aerial vehicle ("UAV") comprising a body structure and at least one support arm. The support arm includes a first arm portion having a first end coupled to the body structure and a second end coupled to a second arm portion. The second arm portion includes a first end coupled to the second end of the first arm portion and a second end coupled to an NDI scanning device. The support arm also includes a compliant member disposed between the first arm portion and the second arm portion. The NDI scanning device includes one or more NDI sensors.

IPC Classes  ?

  • G01M 99/00 - Subject matter not provided for in other groups of this subclass
  • G01N 23/046 - Investigating or analysing materials by the use of wave or particle radiation, e.g. X-rays or neutrons, not covered by groups , or by transmitting the radiation through the material and forming images of the material using tomography, e.g. computed tomography [CT]
  • G01N 23/20008 - Constructional details of analysers, e.g. characterised by X-ray source, detector or optical system; Accessories therefor; Preparing specimens therefor
  • G01B 21/30 - Measuring arrangements or details thereof in so far as they are not adapted to particular types of measuring means of the other groups of this subclass for measuring roughness or irregularity of surfaces
  • G01N 21/88 - Investigating the presence of flaws, defects or contamination
  • G01N 22/02 - Investigating the presence of flaws
  • G01N 27/90 - Investigating or analysing materials by the use of electric, electro-chemical, or magnetic means by investigating magnetic variables for investigating the presence of flaws using eddy currents
  • G01N 29/265 - Arrangements for orientation or scanning by moving the sensor relative to a stationary material

64.

METHOD AND APPARATUS FOR SINGLE-SIDED CLAMP-UP

      
Document Number 03064372
Status Pending
Filing Date 2019-12-10
Open to Public Date 2020-06-21
Owner THE BOEING COMPANY (Canada)
Inventor
  • Oberoi, Harinder S.
  • Barrick, Kevin Marion
  • Hu, Charles Yuanxin

Abstract

Methods and apparatuses for aligning a first hole in a first panel with a second hole in a second panel to define a through-hole. A wall that defines the second hole is gripped from within the through-hole to pull the second panel towards the first panel and thereby establish a clamp-up of the first panel and the second panel.

IPC Classes  ?

  • B23P 19/04 - Machines for simply fitting together or separating metal parts or objects, or metal and non-metal parts, whether or not involving some deformation; Tools or devices therefor so far as not provided for in other classes for assembling or disassembling parts

65.

HIGH-DENSITY ROBOTIC SYSTEM

      
Document Number 03065640
Status Pending
Filing Date 2019-12-19
Open to Public Date 2020-06-21
Owner THE BOEING COMPANY (Canada)
Inventor
  • Oberoi, Harinder S.
  • Barrick, Kevin Marion
  • Hu, Charles Yuanxin

Abstract

Methods and apparatuses for performing automated operations using a high-density robotic cell. An apparatus comprises a first plurality of robotic devices; a second plurality of robotic devices; and a control system. Each of the second plurality of robotic devices is coupled to a single function end effector. The control system controls the second plurality of robotic devices to concurrently perform tasks at a plurality of locations on an assembly, while the first plurality of robotic devices independently maintain a clamp-up at each of the plurality of locations.

IPC Classes  ?

  • G05B 19/418 - Total factory control, i.e. centrally controlling a plurality of machines, e.g. direct or distributed numerical control (DNC), flexible manufacturing systems (FMS), integrated manufacturing systems (IMS), computer integrated manufacturing (CIM)
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
  • B23Q 39/02 - Metal-working machines incorporating a plurality of sub-assemblies, each capable of performing a metal-working operation the sub-assemblies being capable of being brought to act at a single operating station
  • B23Q 41/04 - Features relating to relative arrangements of machines
  • B64C 1/12 - Construction or attachment of skin panels

66.

HIGH-PRESSURE-TORSION APPARATUSES AND METHODS OF MODIFYING MATERIAL PROPERTIES OF WORKPIECES USING SUCH APPARATUSES

      
Document Number 03060065
Status Pending
Filing Date 2019-10-24
Open to Public Date 2020-06-20
Owner THE BOEING COMPANY (Canada)
Inventor Verma, Ravi

Abstract

A high-pressure-torsion apparatus (100), comprising a working axis (102), a first anvil (110), a second anvil (120), and an annular body (130). The annular body (130) comprises a first total-loss convective chiller (140), a second total-loss convective chiller (150), and a heater (160). Each of the first total-loss convective chiller (140) and the second total-loss convective chiller (150) is translatable between the first anvil (110) and the second anvil (120) along the working axis (102), is configured to be thermally convectively coupled with a workpiece (190), and is configured to selectively cool the workpiece (190). The heater (160) is positioned between the first total-loss convective chiller (140) and the second total-loss convective chiller (150) along the working axis (102), is translatable between the first anvil (110) and the second anvil (120) along the working axis (102), and is configured to selectively heat the workpiece (190).

IPC Classes  ?

  • B21D 31/00 - Other methods for working sheet metal, metal tubes, metal profiles

67.

FLUOROPOLYMER ADHESIVES AND METHODS THEREOF

      
Document Number 03065028
Status Pending
Filing Date 2019-12-13
Open to Public Date 2020-06-20
Owner THE BOEING COMPANY (Canada)
Inventor
  • Dustin, Ashley M.
  • Nowak, Andrew P.

Abstract

Examples of the present disclosure provide fluoropolymers and methods for forming and using such fluoropolymers. Fluoropolymers include polyfluorobenzoxazines and polyfluoroimides. Methods for forming polyphthalonitriles are also provided. The present disclosure is further directed to compositions containing one or more fluoropolymers and one or more metal oxides.

IPC Classes  ?

  • C07D 487/04 - Ortho-condensed systems
  • C07C 215/46 - Compounds containing amino and hydroxy groups bound to the same carbon skeleton having hydroxy groups bound to carbon atoms of at least one six-membered aromatic ring and amino groups bound to acyclic carbon atoms or to carbon atoms of rings other than six-membered aromatic rings of the same carbon skeleton
  • C07D 413/06 - Heterocyclic compounds containing two or more hetero rings, at least one ring having nitrogen and oxygen atoms as the only ring hetero atoms containing two hetero rings linked by a carbon chain containing only aliphatic carbon atoms
  • C07D 413/10 - Heterocyclic compounds containing two or more hetero rings, at least one ring having nitrogen and oxygen atoms as the only ring hetero atoms containing two hetero rings linked by a carbon chain containing aromatic rings
  • C08G 73/02 - Polyamines
  • C08G 73/06 - Polycondensates having nitrogen-containing heterocyclic rings in the main chain of the macromolecule; Polyhydrazides; Polyamide acids or similar polyimide precursors
  • C09D 179/02 - Polyamines
  • C09D 179/04 - Polycondensates having nitrogen-containing heterocyclic rings in the main chain; Polyhydrazides; Polyamide acids or similar polyimide precursors
  • C09J 179/02 - Polyamines
  • C09J 179/04 - Polycondensates having nitrogen-containing heterocyclic rings in the main chain; Polyhydrazides; Polyamide acids or similar polyimide precursors

68.

COMPUTER-VISION-BASED AUTONOMOUS OR SUPERVISED-AUTONOMOUS LANDING OF AIRCRAFT

      
Document Number 03058723
Status Pending
Filing Date 2019-10-11
Open to Public Date 2020-06-20
Owner THE BOEING COMPANY (Canada)
Inventor Cramblitt, Robert Merrill

Abstract

An apparatus for supporting an aircraft approaching an airfield runway of an airfield is provided. The apparatus obtains a current pose estimate of the aircraft relative to the airfield runway and determines, based on the current pose estimate of the aircraft, a plurality of proximate poses of the aircraft. The apparatus generates a plurality of images of the airfield runway from a plurality of expected points- of-view of the aircraft and acquires a real-time image of the airfield runway. The apparatus performs a comparison of the real-time image and the plurality of images to identify a best-match image from the plurality of images and generates, based on the best- match image, an updated current pose estimate of the aircraft. The apparatus outputs the updated current pose estimate to a flight control computer of the aircraft, for use in guidance of the aircraft on a final approach.

IPC Classes  ?

  • B64D 45/08 - Landing aids; Safety measures to prevent collision with earth's surface optical
  • G05D 1/10 - Simultaneous control of position or course in three dimensions

69.

AIRCRAFT POSITIONING ON A TAXIWAY

      
Document Number 03065207
Status Pending
Filing Date 2019-12-16
Open to Public Date 2020-06-19
Owner THE BOEING COMPANY (USA)
Inventor
  • Staudinger, Tyler C.
  • Callahan, Kevin S.
  • Chang, Isaac
  • Dame, Stephen
  • Evans, Nick
  • Jorgensen, Zachary
  • Kalin, Joshua
  • Muir, Eric

Abstract

Systems, methods, and computer-readable media storing instructions for determining cross-track error of an aircraft on a taxiway are disclosed herein. The disclosed techniques capture electronic images of a portion of the taxiway using cameras or other electronic imaging devices mounted on the aircraft, pre-process the electronic images to generate regularized image data, apply a trained multichannel neural network model to the regularized image data to generate a preliminary estimate of cross-track error relative to the centerline of the taxiway, and post-process the preliminary estimate to generate an estimate of cross-track error of the aircraft. Further embodiments adjust a GPS-based location estimate of the aircraft using the estimate of cross-track error or adjust the heading of the aircraft based upon the estimate of cross-track error.

IPC Classes  ?

  • B60W 60/00 - Drive control systems specially adapted for autonomous road vehicles
  • B60W 40/02 - Estimation or calculation of driving parameters for road vehicle drive control systems not related to the control of a particular sub-unit related to ambient conditions
  • B64C 19/00 - Aircraft control not otherwise provided for
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • B64D 47/08 - Arrangements of cameras
  • G06N 3/02 - Computer systems based on biological models using neural network models

70.

TRANSFORMABLE SEAT ASSEMBLY

      
Document Number 03056454
Status Pending
Filing Date 2019-09-20
Open to Public Date 2020-06-18
Owner THE BOEING COMPANY (Canada)
Inventor
  • Schultz, John G.
  • Dessalegn, Haftom Y.

Abstract

A transformable seat assembly includes a seat support structure and a back support structure connected to the seat support structure with a hinge defining an axis of rotation. An actuator assembly includes a cylinder and a piston positioned within the cylinder, wherein the cylinder is secured to one of the back support structure or the seat support structure and the piston is secured to other of the one of the back support structure or the seat support structure. Additionally a blocking member is positioned within and adjustable along the cylinder. With blocking member in a first position, piston is limited to travel to a first limit position and the back support structure to a first reclined position. With the blocking member in a second position, piston is limited to travel to a second limit position and back support structure is permitted to rotate to second reclined position.

IPC Classes  ?

  • B60N 2/32 - Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles convertible for other use
  • B60N 2/90 - Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles - Details or parts not otherwise provided for

71.

SYSTEM AND METHOD FOR A HELICAL PRESSURE SNUBBER

      
Document Number 03063002
Status Pending
Filing Date 2019-11-26
Open to Public Date 2020-06-18
Owner THE BOEING COMPANY (Canada)
Inventor Lindahl, Gary M.

Abstract

A snubber includes a head portion, a shank portion, and a threaded portion. The shank portion is attached to the head portion, and the shank portion defines a shank diameter. The threaded portion is attached to the shank portion, and the threaded portion includes an external helical thread wrapped around a central shaft. The external helical thread defines a threaded diameter, and the central shaft defines a central shaft diameter. The shank diameter and the thread diameter are sized such that the shank portion and the threaded portion define at least one fluid flow path when the snubber is installed in a pressure sensor.

IPC Classes  ?

  • F16L 55/05 - Buffers therefor
  • F16L 55/02 - Energy absorbers; Noise absorbers
  • G01L 19/00 - MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE - Details of, or accessories for, apparatus for measuring steady or quasi-steady pressure of a fluent medium insofar as such details or accessories are not special to particular types of pressure gauges

72.

BI-DIRECTIONAL NO-BACK BRAKE PROGRESSIVE MODULATION SPRING SYSTEMS AND METHODS

      
Document Number 03063079
Status Pending
Filing Date 2019-11-27
Open to Public Date 2020-06-18
Owner THE BOEING COMPANY (Canada)
Inventor
  • Bae, Kwan-Ho
  • Gardner, Mark J.
  • Liu, Jen-Shen

Abstract

Methods and systems according to one or more examples are provided for reducing chatter in a no-back brake during aiding load operations. In one example, an apparatus comprises a no-back brake, disposed within an actuator coupled to an aircraft, including a shaft, and a ball ramp plate, coupled to the shaft, to receive a force comprising an air loading force and is displaced responsive to the force. The apparatus further comprises a brake, coupled to the shaft and coupled to the ball ramp plate, and displaced by the ball ramp plate corresponding to a distance the ball ramp plate is displaced. The apparatus further comprises a modulating spring, coupled to the shaft and coupled to the brake, configured to compress in response to the brake being displaced, and the modulating spring is configured to apply a selective compressive force at the brake corresponding to a distance the brake is displaced.

IPC Classes  ?

73.

BRAKE SYSTEMS FOR AIRCRAFT AND RELATED METHODS

      
Document Number 03062120
Status Pending
Filing Date 2019-11-19
Open to Public Date 2020-06-17
Owner THE BOEING COMPANY (Canada)
Inventor
  • Jasklowski, Christopher T.
  • Mackin, Steve G.

Abstract

Braking systems for aircraft are disclosed. An example braking system includes a fan cowl having a leading edge and a trailing edge. The braking system includes a hinge assembly coupled between the leading edge and a fan cage of an aircraft engine to enable the fan cowl to move between a stowed position and a deployed position. An actuator is coupled to the leading edge of the fan cowl, and the actuator is to move the fan cowl via the hinge from the stowed position to the deployed position in a direction away from the aircraft engine and toward a fore end of the aircraft to provide an air brake during a braking event.

IPC Classes  ?

  • B64C 25/42 - Arrangement or adaptation of brakes
  • B64C 9/32 - Air braking surfaces
  • B64D 17/80 - Parachutes in association with aircraft, e.g. for braking thereof
  • B64D 25/00 - Emergency apparatus or devices, not otherwise provided for

74.

SYSTEMS, METHODS, AND APPARATUSES FOR MANAGING ABRASIVE MEDIA IN CAVITATED FLUID

      
Document Number 03061387
Status Pending
Filing Date 2019-11-08
Open to Public Date 2020-06-14
Owner THE BOEING COMPANY (Canada)
Inventor Sanders, Daniel G.

Abstract

Disclosed herein are systems, methods, and appartuses for managing abrasive media in cavitated fluid. One system includes a set of sensors in communication with the cavitated fluid in the processing tank and a processor coupled to the set of sensors. The processor is configured to determine a density of an abrasive media in the cavitated fluid in the processing tank and facilitate maintaining the density of abrasive media in the cavitated fluid in the processing tank at a level that is greater than or equal to a threshold level of abrasive media. A method includes determining a density of abrasive media in the cavitated fluid in the processing tank and maintaining the density of abrasive media in the cavitated fluid in the processing tank at a level that is greater than or equal to a threshold density of abrasive media. One apparatus includes modules for performing the method.

IPC Classes  ?

  • B24C 7/00 - Equipment for feeding abrasive material; Controlling the flowability, constitution, or other physical characteristics of abrasive blasts
  • B24C 9/00 - Appurtenances of abrasive blasting machines or devices, e.g. working chambers, arrangements for handling used abrasive material

75.

INTERLOCKING BLOCKCHAINS FOR AIRCRAFT PART HISTORY AND CURRENT AIRCRAFT CONFIGURATION

      
Document Number 03057092
Status Pending
Filing Date 2019-09-30
Open to Public Date 2020-06-14
Owner THE BOEING COMPANY (Canada)
Inventor Jones, Nicholas William

Abstract

A method and apparatus for recording information for a part, such as history information for an aircraft part. A part history blockchain network comprises part history blockchains for the part that are configured to record the information for the part. Configuration and activity history information for the vehicle is recorded in vehicle configuration and activity history blockchains for the vehicle in a vehicle configuration and activity history blockchain network. A part installation notification is received by the part history blockchain network. The part installation notification identifies the part and indicates that the part is installed on the vehicle. The part history blockchains for the part are locked in response to receiving the part installation notification to prevent adding information for the part to the part history blockchains for the part for as long as the part is installed on the vehicle.

IPC Classes  ?

  • G06F 16/27 - Replication, distribution or synchronisation of data between databases or within a distributed database system; Distributed database system architectures therefor
  • B60S 5/00 - Servicing, maintaining, repairing, or refitting of vehicles
  • B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for

76.

INDUCTION HEATING SYSTEM FOR MOLDING A THERMOPLASTIC ARTICLE AND METHOD FOR MOLDING A THERMOPLASTIC ARTICLE

      
Document Number 03059763
Status Pending
Filing Date 2019-10-23
Open to Public Date 2020-06-12
Owner THE BOEING COMPANY (Canada)
Inventor Gray, Everette D.

Abstract

An induction heating system for molding a thermoplastic article includes a first mold and a second mold defining a mold cavity therebetween for molding the thermoplastic article, a first metallic susceptor as part of or adjacent to the first mold, a first armature- supported induction coil array in proximity to the first metallic susceptor, and a first induction generator electrically coupled with the first armature-supported induction coil array.

IPC Classes  ?

  • B29C 35/08 - Heating or curing, e.g. crosslinking or vulcanising by wave energy or particle radiation

77.

AVIONICS PLUGGABLE ACTIVE OPTICAL CONNECTOR

      
Document Number 03059759
Status Pending
Filing Date 2019-10-23
Open to Public Date 2020-06-11
Owner THE BOEING COMPANY (Canada)
Inventor
  • Truong, Tuong K.
  • Chan, Eric Y.
  • Koshinz, Dennis G.
  • Nguyen, Kim Quan Anh
  • Pang, Henry B.

Abstract

An apparatus configured to function as a pluggable active optical connector that is modular with one or more channels and that converts electrical signals to optical signals and vice versa. On one side, the apparatus has a pluggable electrical interface to a line replaceable unit (LRU); on the other side the apparatus has a pluggable optical interface side to an aircraft fiber optic wiring bundle. The apparatus is pluggable to different types of LRUs including rack-mounted and bolted-down LRUs. The apparatus includes electronic and photonic components sufficient to enable electrical/optical conversion totally within a standard-sized aircraft connector. The apparatus is adaptable to various data communication protocols and has the flexibility to be used in either a single-fiber or a dual-fiber bidirectional data link.

IPC Classes  ?

  • G02B 6/42 - Coupling light guides with opto-electronic elements
  • H04B 10/25 - Arrangements specific to fibre transmission
  • B64D 47/00 - Equipment not otherwise provided for
  • G02B 6/36 - Mechanical coupling means
  • H04J 14/02 - Wavelength-division multiplex systems

78.

ISOLATION COUPLER FOR A STRUCTURAL ASSEMBLY AND METHOD FOR ATTENUATING ALOAD

      
Document Number 03061511
Status Pending
Filing Date 2019-11-12
Open to Public Date 2020-06-10
Owner THE BOEING COMPANY (Canada)
Inventor
  • Aston, Richard W.
  • Langmack, Michael John
  • Tomzynska, Anna M.
  • Herrmann, Matthew
  • Woods, Emily C.

Abstract

An isolation coupler for coupling a functional element to a support structure includes a first bracket. The first bracket includes a number of first-bracket sides. The number of first-bracket sides forms a closed polygonal shape, in plan view. The isolation coupler further includes a number of isolators coupled to each one of the first-bracket sides. The isolation coupler also includes a second bracket. The second bracket includes a number of second-bracket sides. The second bracket sides are coupled to the isolators. The number of second-bracket sides is equal to the number of first-bracket sides and forms the closed polygonal shape, in plan view. The isolators separate each one of the first-bracket sides from a corresponding one of the second-bracket sides to attenuate a load transferred from the first bracket to the second bracket.

IPC Classes  ?

  • F16F 7/00 - Vibration-dampers; Shock-absorbers
  • B64G 1/66 - Arrangements or adaptations of apparatus or instruments, not otherwise provided for
  • F16F 13/00 - Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs

79.

ICE CRYSTAL ICING CONDITION SIMULATION METHOD AND SYSTEM

      
Document Number 03064395
Status Pending
Filing Date 2019-12-09
Open to Public Date 2020-06-10
Owner THE BOEING COMPANY (USA)
Inventor
  • Meis, Charles Steven
  • Langhofer, Erik M.
  • Hass, David Charles
  • Darr, Rachel M.

Abstract

A method and apparatus for simulating icing conditions using a wind tunnel is provided. Water drops are sprayed from a number of nozzles into the wind tunnel. A mist of cryogenic liquid is sprayed into a path of the water drops downwind of the nozzles in the wind tunnel, wherein the mist of cryogenic liquid turns the water drops into ice crystals.

IPC Classes  ?

  • F25C 3/00 - Processes or apparatus specially adapted for producing ice or snow for winter sports or similar recreational purposes, e.g. for sporting installations; Producing artificial snow
  • F25D 3/10 - Devices using other cold materials; Devices using cold-storage bodies using liquefied gases, e.g. liquid air
  • G01M 9/02 - Wind tunnels
  • G01M 9/04 - Wind tunnels - Details

80.

FLIGHT CONTROL SYSTEM FOR DETERMINING ESTIMATED DYNAMIC PRESSURE BASED ON LIFT AND DRAG COEFFICIENTS

      
Document Number 03058899
Status Pending
Filing Date 2019-10-15
Open to Public Date 2020-06-07
Owner THE BOEING COMPANY (Canada)
Inventor
  • Li, Sherwin Chunshek
  • Rupnik, Brian Kenyon
  • Whitehead, Brian
  • Najmabadi, Kioumars

Abstract

A flight control system for an aircraft is disclosed. The flight control system includes one or more processors and a memory coupled to the processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the flight control system to receive as input a plurality of first operating parameters that each represent an operating condition of the aircraft. The flight control system is further caused to determine a drag coefficient and a lift coefficient based on the plurality first of operating parameters. The flight control system is also caused to determine an estimated dynamic pressure based on both the drag coefficient and the lift coefficient.

IPC Classes  ?

  • G01M 17/00 - Testing of vehicles
  • B64D 43/00 - Arrangements or adaptations of instruments
  • G01C 9/00 - Measuring inclination, e.g. by clinometers, by levels
  • G01C 25/00 - Manufacturing, calibrating, cleaning, or repairing instruments or devices referred to in the other groups of this subclass
  • G01P 21/00 - Testing or calibrating of apparatus or devices covered by the other groups of this subclass

81.

APPARATUS AND METHODS FOR CONNECTING A FIRST ELECTRICALLY CONDUCTIVE TUBE AND A SECOND ELECTRICALLY CONDUCTIVE TUBE

      
Document Number 03061728
Status Pending
Filing Date 2019-11-14
Open to Public Date 2020-06-07
Owner THE BOEING COMPANY (Canada)
Inventor Gilbertson, Michael L.

Abstract

An apparatus includes first and second electrically conductive tubes, first and second electrical isolators, and a nut. The first electrical isolator has a central passageway. The first electrically conductive tube has a flared end disposed around the first electrical isolator. The flared end includes external threads. The second electrically conductive tube has an outer flange. The second electrical isolator is disposed around the second electrically conductive tube and engages the outer flange. The nut is disposed around the second electrically conductive tube and engages the second electrical isolator. The nut includes internal threads corresponding to the external threads of the flared end of the first electrically conductive tube.

IPC Classes  ?

  • H01R 4/56 - Electrically-conductive connections between two or more conductive members in direct contact, i.e. touching one another; Means for effecting or maintaining such contact; Electrically-conductive connections having two or more spaced connecting locations for conductors and using contact members penetrating insulation one conductor screwing into another
  • F16L 25/01 - Construction or details of pipe joints not provided for in, or of interest apart from, groups specially adapted for realising electrical conduction between the two pipe ends of the joint or between parts thereof
  • H01R 13/622 - Screw-ring or screw-casing

82.

DYNAMIC PATHLOSS MITIGATION

      
Document Number 03056046
Status Pending
Filing Date 2019-09-19
Open to Public Date 2020-06-06
Owner THE BOEING COMPANY (Canada)
Inventor
  • Johnston, Matthew
  • Jahne, Seth
  • Griswold, Adam Lee

Abstract

Aspects provide for dynamic pathloss mitigation via a cross layer tool chain by simulating a three-dimensional model of a physical environment including an Access Point, an End Point running an application, and a passive object; emulating network traffic for the application transmitted between the Access Point and the End Point; simulating, in the model, pathways for signals to carry the traffic in a plurality of regions for the physical environment; emulating signal degradation along the pathways in the plurality of regions based on respective locations for the Access Point, the End Point, and the passive object in the physical environment; and in response to the signal degradation satisfying a pathloss threshold, outputting a command to the application to affect operations of the End Point. Additionally, the cross layer tool chain outputs a Graphical User Interface showing a signal degradation map based on the simulated network traffic overlaid on the model.

IPC Classes  ?

  • H04W 24/02 - Arrangements for optimising operational condition
  • H04W 40/18 - Communication route or path selection, e.g. power-based or shortest path routing based on predicted events
  • H04W 64/00 - Locating users or terminals for network management purposes, e.g. mobility management

83.

SYSTEMS AND METHODS TO PRODUCE AIRCRAFT CABIN SUPPLY AIR

      
Document Number 03058732
Status Pending
Filing Date 2019-10-11
Open to Public Date 2020-06-06
Owner THE BOEING COMPANY (Canada)
Inventor
  • Richardson, Marcus K.
  • Mackin, Steve G.

Abstract

Systems to produce cabin supply air for aircraft and related methods are described herein. An example system includes an air conditioning pack including a heat exchanger including a first flow path and a second flow path isolated from the first flow path. The second flow path is to receive cabin exhaust air from a cabin of an aircraft. The cabin exhaust air is to reduce a temperature of the cabin supply air flowing through the first flow path of the heat exchanger. The system also includes a turbine to receive the cabin supply air from the heat exchanger. The turbine is to reduce a temperature and pressure of the cabin supply air. A turbine outlet of the turbine is fluidly coupled to the cabin to provide the cabin supply air to the cabin. The system further includes a fan to direct the cabin exhaust air from the heat exchanger.

IPC Classes  ?

  • B64D 13/00 - Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
  • F24F 5/00 - Air-conditioning systems or apparatus not covered by group or

84.

METHODS OF TESTING A MONUMENT THAT IS TO BE ATTACHED TO A FLOOR OF AN AIRCRAFT

      
Document Number 03063867
Status Pending
Filing Date 2019-12-05
Open to Public Date 2020-06-05
Owner THE BOEING COMPANY (Canada)
Inventor Smirnov, Alexey N.

Abstract

Methods of testing a monument that is attached to a floor of the aircraft. The testing uses a compliance matrix based on attachment points where the monument is attached to the floor of the aircraft. The testing uses a test monument that is equipped with extension members and load cells positioned at the corresponding attachment points. A test load is applied to the test monument and reaction loads are determined at each attachment point. During the test period, the compliance matrix and reaction loads are used to calculate displacements at each attachment point. Each of the extension members are then adjusted by the corresponding displacement. At the end of the test period, determination is made as to whether the test monument is capable of sustaining the predetermined load and adjusted displacements at the attachment points.

IPC Classes  ?

  • G01N 3/00 - Investigating strength properties of solid materials by application of mechanical stress
  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • B64C 1/18 - Floors
  • B64D 11/00 - Passenger or crew accommodation; Flight-deck installations not otherwise provided for

85.

COMPUTER SYSTEM INTEGRITY THROUGH A COMBINATION OF CERTIFIABLE AND QUALIFIABLE SOFTWARE

      
Document Number 03061941
Status Pending
Filing Date 2019-11-15
Open to Public Date 2020-06-04
Owner THE BOEING COMPANY (Canada)
Inventor Sanders-Reed, John Newell

Abstract

A method of improving integrity of a computer system includes executing certifiable and qualifiable software applications. The certifiable software application is composed of static program instructions executed sequentially to process input data to produce an output, and the qualifiable software application uses a model iteratively built using a machine learning algorithm to process the input data to produce a corresponding output. The certifiable software application is certifiable for the computer system according to a certification standard, and the qualifiable software application being non-certifiable for the computer system according to the certification standard. The method also includes cross-checking the output by comparison with the corresponding output to verify the output, and thereby improve integrity of the computer system. And the method includes generating an alert that the output is unverified when the comparison indicates that the output differs from the corresponding output by more than a threshold.

IPC Classes  ?

  • G06F 21/57 - Certifying or maintaining trusted computer platforms, e.g. secure boots or power-downs, version controls, system software checks, secure updates or assessing vulnerabilities

86.

SYSTEM AND METHOD FOR OPTIMIZING A CRUISE VERTICAL PROFILE SUBJECT TO A TIME-OF-ARRIVAL CONSTRAINT

      
Document Number 03055980
Status Pending
Filing Date 2019-09-19
Open to Public Date 2020-05-28
Owner THE BOEING COMPANY (Canada)
Inventor
  • De Prins, Johan L.
  • Figlar, Bastian
  • Garrido-Lopez, David
  • Scharl, Julien
  • Yochum, Thomas E.

Abstract

A system and a method for planning and flying a cost-optimal cruise vertical profile in combination with a required time-of-arrival (RTA) constraint. The method may be implemented as a single function in a flight management system (FMS). The FMS (10) plans the aircraft trajectory with cruise vertical and speed profiles that are optimized to minimize flight cost (e.g., fuel burn) while meeting the time constraint. When appropriate under the circumstances, this integrated function is also able to degrade the cruise vertical profile in order to open the window of achievable RTAs and increase the RTA success rate. The method also monitors progress of the flight along the planned trajectory as actual flight conditions may differ from the forecasted flight conditions, and readapts the cruise speed profile when the estimated arrival time is deviating from the RTA constraint by more than a specified threshold.

IPC Classes  ?

  • G08G 5/00 - Traffic control systems for aircraft
  • G05D 1/10 - Simultaneous control of position or course in three dimensions

87.

LAVATORY OCCUPANCY DETECTION SYSTEMS AND METHODS

      
Document Number 03058749
Status Pending
Filing Date 2019-10-15
Open to Public Date 2020-05-28
Owner THE BOEING COMPANY (Canada)
Inventor Alvarez, Christopher

Abstract

An occupancy detection system and method for a lavatory includes a door sensor operatively coupled to a door of the lavatory. The door sensor is configured to output a door sensor signal that indicates a status of the door. At least one presence sensor that is configured to output at least one presence sensor signal that indicates an occupancy status of the lavatory. An occupancy detection control unit is in communication with the door sensor and the at least one presence sensor. The occupancy detection control unit is configured to receive the door sensor signal and the presence sensor signal(s). The occupancy detection control unit is configured to determine an occupancy status of the lavatory based on the door sensor signal and the presence sensor signal(s).

IPC Classes  ?

  • A47K 11/00 - Closets without flushing; Urinals without flushing; Chamber pots; Chairs with toilet conveniences or specially adapted for use with toilets
  • B64D 11/02 - Toilet fittings

88.

HEATING CIRCUIT LAYOUT FOR SMART SUSCEPTOR INDUCTION HEATING APPARATUS

      
Document Number 03055543
Status Pending
Filing Date 2019-09-16
Open to Public Date 2020-05-27
Owner THE BOEING COMPANY (Canada)
Inventor
  • Voss, Bret A.
  • Matsen, Marc R.
  • Olberg, Jeffrey H.
  • Spalding, John F.
  • Jones, James R.

Abstract

A heating apparatus (20) for thermally processing a part (21) includes a table (40) formed of a thermally conductive material and a table inductive heating circuit (52 or 121) thermally coupled to the table (40). The table inductive heating circuit (52 or 121) comprising a plurality of table induction coil circuits (62 or 122, 124) electrically coupled in parallel with each other. Each table induction coil circuit (62 or 122, 124) includes a table electrical conductor (70) and a table smart susceptor (72) having a Curie temperature. First and second table induction coil circuits have pairs of segments positioned adjacent each other that are configured to carry current in opposite directions. In some examples, the table induction coil circuits have partially nested, rectilinear hook shapes. In other examples, the table induction coil circuits overlap each other at rhombus-shaped turns.

IPC Classes  ?

  • H05B 6/10 - Induction heating apparatus, other than furnaces, for specific applications
  • H05B 6/36 - Coil arrangements

89.

SYSTEM AND METHOD FOR GENERATING AN AIRCRAFT FAULT PREDICTION CLASSIFIER

      
Document Number 03061041
Status Pending
Filing Date 2019-11-06
Open to Public Date 2020-05-27
Owner THE BOEING COMPANY (Canada)
Inventor
  • Sundareswara, Rashmi
  • Betz, Franz David
  • Lu, Tsai-Ching

Abstract

A method includes receiving input data including a plurality of feature vectors and labeling each feature vector based on a temporal proximity of the feature vector to occurrence of a fault. Feature vectors that are within a threshold temporal proximity to the occurrence of the fault are labeled with a first label value and other feature vectors are labeled with a second label value. The method includes determining, for each feature vector of a subset, a probability that the label associated with the feature vector is correct. The subset includes feature vectors having labels that indicate the first label value. The method includes reassigning labels of one or more feature vectors of the subset having a probability that fails to satisfy a probability threshold and, after reassigning the labels, training an aircraft fault prediction classifier using supervised training data including the plurality of feature vectors and the labels.

IPC Classes  ?

  • G01M 17/00 - Testing of vehicles
  • G06N 20/00 - Machine learning
  • B64D 47/00 - Equipment not otherwise provided for
  • B64F 5/00 - Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for

90.

EME PROTECTION CAP SYSTEM WITH PUSH SEALANT EXTRUSION MECHANISM

      
Document Number 03059451
Status Pending
Filing Date 2019-10-18
Open to Public Date 2020-05-20
Owner THE BOEING COMPANY (Canada)
Inventor
  • Auffinger, Sean
  • Stevens, Bart

Abstract

A cap assembly for enclosing a metallic fastener which extends through a structure. The assembly includes a housing having an inner wall and an outer wall which extends about and is spaced apart from the inner wall defining a space positioned between the inner wall and outer wall. The assembly further includes a plunger member with a side wall portion secured to an end wall portion. The side wall portion of the plunger member has a thickness dimension smaller than a distance between the inner wall and the outer wall to position the sidewall portion of the plunger member within the space. With the side wall portion positioned within the space, the end wall portion is positioned in alignment with the inner wall and with an opening defined by and through the inner wall.

IPC Classes  ?

  • F16B 37/14 - Cap nuts; Nut caps or bolt caps
  • B64D 45/02 - Lightning protectors; Static dischargers

91.

EASY LOCK P-CLAMP

      
Document Number 03060749
Status Pending
Filing Date 2019-10-29
Open to Public Date 2020-05-20
Owner THE BOEING COMPANY (Canada)
Inventor
  • Kim, Jin Heung
  • Seo, Jin-Seog

Abstract

A clamp assembly for securing wire bundles to a structure having a body and a strap hinged to the body having an axis of rotation. The body has a ramp with a surface and has a latch wall portion. The strap has a locking wall portion wherein a radial distance from the surface to the axis of rotation decreases as the surface extends in a direction away from the strap such that with the strap in contact with the surface and slid along in contact with the surface, the strap resiliently bends in a direction toward the a first end of the strap. With the strap moved beyond the surface, the strap resiliently bends in a direction away from the first end of the strap, placing the locking wall portion in abutting relationship with the latch wall portion and positioning the strap and the body in a closed locked position.

IPC Classes  ?

  • F16L 3/13 - Supports for pipes, cables or protective tubing, e.g. hangers, holders, clamps, cleats, clips, brackets substantially surrounding the pipe, cable or protective tubing comprising a member substantially surrounding the pipe, cable or protective tubing and engaging it by snap action
  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
  • H02G 3/32 - Installations of cables or lines on walls, floors or ceilings using mounting clamps

92.

SHEAR TIES FOR AIRCRAFT WING

      
Document Number 03060450
Status Pending
Filing Date 2019-10-28
Open to Public Date 2020-05-19
Owner THE BOEING COMPANY (Canada)
Inventor
  • Linton, Kim A.
  • Baraja, Jaime E.
  • Wu, Hsi-Yung T.

Abstract

An example aircraft wing includes a skin, a composite shear tie, a stringer base charge overlaying the skin, and a stringer overlaying the stringer base charge. The composite shear tie includes a shear-tie web, a first shear-tie flange extending from a first side of the shear-tie web, a second shear-tie flange extending from a second side of the shear-tie web, and a first shear-tie tab extending from an end of the first side of the shear-tie web. The stringer includes a stringer web, a first stringer flange extending from a first side of the stringer web, and a second stringer flange extending from a second side of the stringer web. The first stringer flange is stitched to and integrated with the stringer base charge and the skin. Further, the first shear-tie flange is stitched to and integrated with the first stringer flange.

IPC Classes  ?

  • B64C 3/18 - Spars; Ribs; Stringers
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
  • B64C 3/26 - Construction, shape, or attachment of separate skins, e.g. panels

93.

SYSTEM AND METHOD FOR LAMINATING A COMPOSITE LAMINATE ALONG A CONTINUOUSLOOP LAMINATION PATH

      
Document Number 03053465
Status Pending
Filing Date 2019-08-29
Open to Public Date 2020-05-13
Owner THE BOEING COMPANY (Canada)
Inventor
  • Shaw, Paul D.
  • Kendall, James R.
  • Suriyaarachchi, Raviendra S.

Abstract

A manufacturing system includes a plurality of lamination heads and a head- moving system defining a continuous loop lamination path configured to move the lamination heads in series along the lamination path. The manufacturing system also includes at least one lamination mandrel positioned along a portion of the lamination path. The lamination heads are each configured to dispense a layup material onto the at least one lamination mandrel or onto layup material previously applied onto the lamination mandrel while the lamination heads are moved by the head-moving system through one or more revolutions of the lamination path to lay up a composite laminate.

IPC Classes  ?

  • B32B 39/00 - Layout of apparatus or plants, e.g. modular laminating systems
  • B32B 37/00 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding

94.

EME CAP FOR PREVENTING UNCURED SEALANT SQUEEZE OUT

      
Document Number 03059452
Status Pending
Filing Date 2019-10-18
Open to Public Date 2020-05-09
Owner THE BOEING COMPANY (Canada)
Inventor
  • Hansen, Darrin M.
  • Hargrave, Benjamin P.
  • Pajel, Carissa

Abstract

A containment apparatus for enclosing a metallic fastener extending through a structure includes a cap member. The cap member includes a first wall member which defines a first cavity and a first end. The first end defines a first opening providing access into the first cavity for at least a portion of the metallic fastener. The cap member further includes a second wall member secured to and extends from an exterior surface of the first wall member. The second wall member extends spaced apart from and along the first wall member to a first end. The second wall member surrounds the first wall member such that first wall member and second wall member form a second cavity positioned between the first wall member and the second wall member. The first end of the first wall member and the first end of the second wall member are coplanar with one another.

IPC Classes  ?

95.

ESTABLISHING ELECTRONICS IN COMPOSITE PARTS BY LOCATING ELECTRONICS ON LAY-UP MANDRELS

      
Document Number 03060288
Status Pending
Filing Date 2019-10-25
Open to Public Date 2020-05-08
Owner THE BOEING COMPANY (Canada)
Inventor
  • Fay, Matthew K.
  • Humfeld, Keith D.

Abstract

A method for forming composite materials and associated apparatuses is presented, including positioning at least one electronic component on a lay-up surface. The method also includes positioning a composite on the lay-up surface, where the composite comprises resin and fibers. Additionally, the method includes causing a flow of the resin between the lay-up surface and the fibers. Yet further, the method includes curing the resin to form a cured resin, where the electronic component and the fibers are located in the cured resin. The composite material includes a resin having a shape based on a surface of a lay-up system. Additionally, the composite material includes fibers contained within the resin. Further, the composite materials includes at least one electronic component. The electronic component of the composite material is located in the resin based on a flow of the resin around the electronic component on the surface of the lay-up.

IPC Classes  ?

  • H05K 3/30 - Assembling printed circuits with electric components, e.g. with resistor
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
  • B64C 1/12 - Construction or attachment of skin panels
  • H05K 3/12 - Apparatus or processes for manufacturing printed circuits in which conductive material is applied to the insulating support in such a manner as to form the desired conductive pattern using printing techniques to apply the conductive material
  • H05K 3/28 - Applying non-metallic protective coatings
  • B32B 27/04 - Layered products essentially comprising synthetic resin as impregnant, bonding, or embedding substance

96.

MONOLITHIC OUTBOARD GEAR BEAM SUPPORT FITTING

      
Document Number 03053553
Status Pending
Filing Date 2019-08-29
Open to Public Date 2020-05-07
Owner THE BOEING COMPANY (Canada)
Inventor
  • Kamila, Eric Sean
  • Palmer, Benjamin Joseph
  • Heer, Steven Scott

Abstract

A breakaway support configured to selectively release an actuator from a fitting and a method of providing the breakaway support. The breakaway support includes a race positioned between the actuator and the fitting. The second end of the actuator is connected to the fitting via a ball joint is positioned within the race. The ball joint permits the actuator to pivot about the ball joint in a vertical plane between a first position and a second position. The breakaway support includes a first knuckle that causes the actuator to release from the fitting when the actuator moves in a first direction beyond the first position. A portion of the fitting or a second knuckle may cause the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. A portion of the actuator may break to release the actuator from the fitting.

IPC Classes  ?

  • F16C 11/06 - Ball-joints; Other joints having more than one degree of angular freedom, i.e. universal joints
  • B64C 25/10 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
  • F16C 7/00 - Connecting-rods or like links pivoted at both ends; Construction of connecting-rod heads

97.

MULTIFUNCTIONAL BATTERY PACKAGING AND INSULATION

      
Document Number 03061040
Status Pending
Filing Date 2019-11-06
Open to Public Date 2020-05-07
Owner THE BOEING COMPANY (Canada)
Inventor Polus, Jeffrey E.

Abstract

Systems, methods, and apparatus for multifunctional battery packaging and insulation are disclosed. In one or more embodiments, a battery pack comprises a plurality of battery cells. The battery pack further comprises a block comprising a plurality of recesses formed within the block. In one or more embodiments, each of the recesses respectively houses one of the battery cells within the block. In at least one embodiment, the block comprises a low density ceramic fiber reinforced foam that is porous such that a gas or liquid may pass through the block to cool the battery pack. In one or more embodiments, at least a portion of the block is covered with a ceramic matrix composite (CMC) material comprising a ceramic slurry composite pre-impregnated (prepreg) with fibers. In some embodiments, the CMC material is cured via kiln firing the block.

IPC Classes  ?

  • H01M 2/02 - Cases, jackets or wrappings
  • H01M 10/613 - Cooling or keeping cold
  • H01M 10/6557 - Solid parts with flow channel passages or pipes for heat exchange arranged between the cells

98.

METHODS, APPARATUSES, AND SYSTEMS FOR SMART DELIVERY OF COATING MATERIAL

      
Document Number 03059691
Status Pending
Filing Date 2019-10-22
Open to Public Date 2020-05-02
Owner THE BOEING COMPANY (Canada)
Inventor
  • She, Chunxing
  • Gayle, David Michael

Abstract

Methods, systems and apparatuses are disclosed for controlling the release of a coating material to a substrate surface, with the system and apparatuses emulating an experienced human artisan by sensing condition parameters and substrate parameters and comparing parameters to stored parameter values and value ranges.

IPC Classes  ?

  • B05B 12/14 - Arrangements for controlling delivery; Arrangements for controlling the spray area for supplying a selected one of a plurality of liquids or other fluent materials to a single spray outlet

99.

SYSTEM AND METHOD FOR CONCURRENTLY LAMINATING AND TRIMMING A COMPOSITE LAMINATE

      
Document Number 03053492
Status Pending
Filing Date 2019-08-29
Open to Public Date 2020-05-01
Owner THE BOEING COMPANY (Canada)
Inventor
  • Modin, Andrew E.
  • Willden, Kurtis S.
  • Jones, Darrell D.

Abstract

A manufacturing system includes a plurality of lamination heads statically positioned in end-to-end relation to each other and defining a lamination station, and configured to dispense a layup material along a dispensing direction. The manufacturing system also includes a lamination surface movable underneath the lamination station. The lamination heads are configured to sequentially apply the layup material onto the lamination surface and onto previously applied layup material as the lamination surface passes through the lamination station to thereby form a composite laminate having a stack of composite plies arranged in a desired ply stacking sequence defined by positions of the lamination heads relative to each other within the lamination station. The manufacturing system further includes one or more trimming devices configured to trim the composite laminate.

IPC Classes  ?

  • B32B 39/00 - Layout of apparatus or plants, e.g. modular laminating systems
  • B32B 37/00 - Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
  • B32B 38/00 - Ancillary operations in connection with laminating processes

100.

APPARATUSES AND METHODS FOR DISPENSING FLOWABLE MATERIALS

      
Document Number 03052166
Status Pending
Filing Date 2019-08-14
Open to Public Date 2020-04-30
Owner THE BOEING COMPANY (Canada)
Inventor
  • Pringle, John W., Iv
  • Davancens, Angelica
  • Sarh, Branko

Abstract

An apparatus for dispensing a flowable material is disclosed. The apparatus comprises a rotary actuator, a reservoir, containing a hydraulic fluid, a piston, movable inside the reservoir, a linear actuator, coupled to the piston, a gear train, coupling the rotary actuator with the linear actuator, and a flowable-material dispenser, hydraulically coupled with the reservoir.

IPC Classes  ?

  • B05C 5/00 - Apparatus in which liquid or other fluent material is projected, poured or allowed to flow on to the surface of the work
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