The Boeing Company

United States of America

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New (last 4 weeks) 148
2020 November (MTD) 131
2020 October 130
2020 September 100
2020 August 80
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IPC Class
B64C 1/06 - Frames; Stringers; Longerons 350
B29L 31/30 - Vehicles, e.g. ships or aircraft, or body parts thereof 321
G06F 19/00 - Digital computing or data processing equipment or methods, specially adapted for specific applications (specially adapted for specific functions G06F 17/00;data processing systems or methods specially adapted for administrative, commercial, financial, managerial, supervisory or forecasting purposes G06Q;healthcare informatics G16H) 309
B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like 297
B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor 290
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Status
Pending 2,066
Registered / In Force 12,936
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1.

ACTIVE-PRESSURE HOLE FINISHING TOOL

      
Application Number 16422435
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Albrecht, Mark
  • Chan, Kwok Tung

Abstract

Provided is cutting tool. The tool, in certain examples, includes a drill body that defines a drill axis, and a tool window formed in the drill body. The tool also includes a drill bit extending from the drill body, and a material reworking attachment (“MRA”) coupled to the drill body and storable within the tool window. The MRA is extendable from a stored position into either a surface-finishing position or a material-removal position. The MRA includes a first chamfering blade, a second chamfering blade, and a finishing surface interposed between the chamfering blades. The tool also includes a position manager to detect a position of the cutting tool with reference to a workpiece, and an actuator to transition the MRA from the stored position to the material-removal position, followed by a transition to the surface-finishing position, and followed by a transition to material-removal position.

IPC Classes  ?

2.

Non-Destructive Inspection Methods, Systems and Apparatuses Using Focusable X-Ray Backscatter Detectors

      
Application Number 16419293
Status Pending
Filing Date 2019-05-22
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Safai, Morteza

Abstract

Methods, apparatuses, and systems are disclosed for generating X-ray backscatter images of a target by employing a flexible, deformable and flexible X-ray backscatter detector comprising a scintillating material layer comprising a scintillating jet print ink.

IPC Classes  ?

  • G01N 23/20008 - Constructional details of analysers, e.g. characterised by X-ray source, detector or optical system; Accessories therefor; Preparing specimens therefor
  • G01N 23/203 - Measuring back scattering

3.

CONDUITS FOR TRANSPORTING FLUIDS AND METHODS OF FABRICATING THE SAME

      
Application Number 16992437
Status Pending
Filing Date 2020-08-13
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Di Carlo, Tony
  • Vaniman, Brian T.
  • Leuer, John P.

Abstract

A method of fabricating a conduit comprises simultaneously corrugating three plies to form a bellows. The method also comprises simultaneously trimming a corrugated inboard ply and a first corrugated outboard ply of the bellows. The method further comprises locating a weld-through ring and a second weld-through ring between the corrugated inboard ply and the first corrugated outboard ply. The method additionally comprises forming a port and a second port through the weld-through ring and the second weld-through ring, respectively. The method also comprises communicatively coupling a sensor and a second sensor with an interstitial space, interposed between the corrugated inboard play and the first corrugated outboard ply, via the port and the second port, respectively.

IPC Classes  ?

  • F16L 5/02 - Sealing
  • F16L 27/111 - Adjustable joints; Joints allowing movement comprising a flexible connection only the ends of the pipe being interconnected by a flexible sleeve the sleeve having the form of a bellows with multiple corrugations the bellows being reinforced
  • G01M 3/18 - Investigating fluid tightness of structures by using fluid or vacuum by detecting the presence of fluid at the leakage point using electric detection means for valves

4.

NANO-METAL CONNECTIONS FOR A SOLAR CELL ARRAY

      
Application Number 16991589
Status Pending
Filing Date 2020-08-12
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Rehder, Eric

Abstract

An electrical connection is formed between first and second conductive elements, by inserting a nano-metal material between the first and second conductive elements; and heating the nano-metal material to a melting temperature to form the electrical connection between the first and second conductive elements. The nano-metal material may comprise a nano-metal paste or ink comprised of one or more of Gold (Au), Copper (Cu), Silver (Ag), and/or Aluminum (Al) nano-particles that melt or fuse into a solid to form the electrical connection, at a melting temperature of about 150-250 degrees C., and more preferably, about 175-225 degrees C. The electrical connection may be formed between a solar cell and a substrate by creating a via in the solar cell between a front and back side of the solar cell, wherein the via is connected to a contact on the front side of the solar cell and a trace on the substrate.

IPC Classes  ?

  • H01L 31/042 - PV modules or arrays of single PV cells
  • H01L 31/0224 - Electrodes
  • H01L 31/05 - Electrical interconnection means between PV cells inside the PV module, e.g. series connection of PV cells
  • H01L 27/142 - Energy conversion devices
  • H01L 31/0443 - PV modules or arrays of single PV cells including bypass diodes comprising bypass diodes integrated or directly associated with the devices, e.g. bypass diodes integrated or formed in or on the same substrate as the photovoltaic cells
  • H01L 31/044 - PV modules or arrays of single PV cells including bypass diodes
  • H01L 31/02 - SEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR - Details thereof - Details
  • H01L 31/0352 - SEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR - Details thereof characterised by their semiconductor bodies characterised by their shape or by the shapes, relative sizes or disposition of the semiconductor regions
  • H02S 40/34 - Electrical components comprising specially adapted electrical connection means to be structurally associated with the PV module, e.g. junction boxes
  • H01L 21/02 - Manufacture or treatment of semiconductor devices or of parts thereof
  • H01L 31/0392 - SEMICONDUCTOR DEVICES; ELECTRIC SOLID STATE DEVICES NOT OTHERWISE PROVIDED FOR - Details thereof characterised by their semiconductor bodies characterised by their crystalline structure or particular orientation of the crystalline planes including thin films deposited on metallic or insulating substrates
  • H01L 31/0687 - Multiple junction or tandem solar cells
  • H01L 31/048 - Encapsulation of modules

5.

APPARATUSES AND METHODS FOR APPLYING PRESSURE TO EDGE SURFACES

      
Application Number 16421904
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Howard, Jesse P.

Abstract

An apparatus (100) for applying pressure to at least a portion of an edge surface (192), which bridges opposing faces (194) of a workpiece (190), comprises a frame (110), a first roller (120), a second roller (130), a rotation-control member (140), a first biasing member (150), and a second biasing member (160). The first roller (120) and the second roller (130) are coupled to the frame (110), rotatable relative to the frame (110) about a first pivot axis (125), and translationally fixed relative to the frame (110). The rotation-control member (140) is movable relative to the frame (110), controlling rotation of the first roller (120) and the second roller (130) relative to the frame (110). The first biasing member (150) is coupled to the frame (110) and is configured to operate in tension. The second biasing member (160) is positioned, in compression, between the frame (110) and the rotation-control member (140).

IPC Classes  ?

  • B21B 1/16 - Metal rolling methods or mills for making semi-finished products of solid or profiled cross-section; Sequence of operations in milling trains; Layout of rolling-mill plant, e.g. grouping of stands; Succession of passes or of sectional pass alternations for rolling wire or material of like small cross-section
  • B21B 39/14 - Guiding, positioning or aligning work

6.

APPARATUSES AND METHODS FOR APPLYING PRESSURE TO EDGE SURFACES

      
Application Number 16421900
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Howard, Jesse P.

Abstract

An apparatus (100) for applying pressure to at least a portion of an edge surface (192) of a workpiece (190) comprises a frame (110), a first roller (120), a second roller (130), a rotation-control member (140), a first biasing member (150), and a second biasing member (160). The first roller (120) and the second roller (130) are coupled to and are rotatable relative to the frame (110) while at least one of the first roller (120) or the second roller (130) is translatable relative to the frame (110). The rotation-control member (140) is coupled to and is movable relative to the frame (110), controlling rotation of the first roller (120) and the second roller (130). The first biasing member (150) is coupled to the first roller (120) and to the second roller (130) and configured to operate in tension. The second biasing member (160) is positioned, in compression, between the frame (110) and the rotation-control member (140).

IPC Classes  ?

  • B30B 3/04 - Presses characterised by the use of rotary pressing members, e.g. rollers, rings, discs co-operating with one another, e.g. with co-operating cones
  • B30B 9/28 - Presses specially adapted for particular purposes for forming shaped articles
  • B30B 11/00 - Presses specially adapted for forming shaped articles from material in particulate or plastic state, e.g. briquetting presses or tabletting presses
  • B30B 9/24 - Presses specially adapted for particular purposes for squeezing-out liquid from liquid-containing material, e.g. juice from fruits, oil from oil-containing material using an endless pressing band

7.

APPARATUSES AND METHODS FOR APPLYING PRESSURE TO EDGE SURFACES

      
Application Number 16421912
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Howard, Jesse P.

Abstract

An apparatus (100) for applying pressure to an edge surface (192) comprises a frame (110), a first roller (120), a second roller (130), a rotation-control member (140), a first biasing member (150), and a second biasing member (160). The first roller (120) and the second roller (130) are coupled to the frame (110) and are rotatable relative to the frame (110). At least one of the first roller (120) or the second roller (130) is translatable relative to the frame (110). The rotation-control member (140) is movable relative to the frame (110), controlling rotation of the first roller (120) and the second roller (130) relative to the frame (110). The first biasing member (150) is coupled to the frame (110) and is configured to operate in tension. The second biasing member (160) is positioned, in compression, between the frame (110) and the rotation-control member (140).

IPC Classes  ?

  • B30B 3/04 - Presses characterised by the use of rotary pressing members, e.g. rollers, rings, discs co-operating with one another, e.g. with co-operating cones
  • B30B 9/28 - Presses specially adapted for particular purposes for forming shaped articles
  • B30B 9/24 - Presses specially adapted for particular purposes for squeezing-out liquid from liquid-containing material, e.g. juice from fruits, oil from oil-containing material using an endless pressing band
  • B30B 11/00 - Presses specially adapted for forming shaped articles from material in particulate or plastic state, e.g. briquetting presses or tabletting presses

8.

APPARATUSES AND METHODS FOR APPLYING PRESSURE TO EDGE SURFACES

      
Application Number 16421935
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Howard, Jesse P.

Abstract

An apparatus (100) for applying pressure to at least a portion of an edge surface (192), which bridges opposing faces (194) of a workpiece (190), comprises a frame (110), a first roller (120), a second roller (130), a rotation-control member (140), a first biasing member (150), and a second biasing member (160). The first roller (120) and the second roller (130) are coupled to the frame (110) and are rotatable relative to the frame (110). At least one of the first roller (120) or the second roller (130) is translatable relative to the frame (110) along a first axis (101). The rotation-control member (140) is movable relative to the frame (110), controlling rotation of the first roller (120) and the second roller (130) relative to the frame (110). The first biasing member (150) is configured to operate in compression along a second axis (102). The second biasing member (160) is positioned, in compression, between the frame (110) and the rotation-control member (140).

IPC Classes  ?

  • B30B 3/04 - Presses characterised by the use of rotary pressing members, e.g. rollers, rings, discs co-operating with one another, e.g. with co-operating cones
  • B30B 9/28 - Presses specially adapted for particular purposes for forming shaped articles
  • B30B 9/24 - Presses specially adapted for particular purposes for squeezing-out liquid from liquid-containing material, e.g. juice from fruits, oil from oil-containing material using an endless pressing band
  • B30B 11/00 - Presses specially adapted for forming shaped articles from material in particulate or plastic state, e.g. briquetting presses or tabletting presses

9.

Optical Imaging and Scanning of Holes

      
Application Number 16419478
Status Pending
Filing Date 2019-05-22
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Khosravani, Shahriar

Abstract

Methods and apparatus for optical imaging and scanning of holes machined, drilled or otherwise formed in a substrate made of composite or metallic material. The method utilizes an optical instrument for imaging and scanning a hole in combination with an image processor configured (e.g., programmed) to post-process the image data to generate one complete planarized image without conical optical distortion. The optical instrument includes an optical microscope with confocal illumination and a conical mirror axially positioned to produce a full 360-degree sub-image with conical distortion. In the post-processing step, a mathematical transformation in the form of computer-executable code is used to transform the raw conical sub-images to planar sub-images. The planarized sub-images may be stitched together to form a complete planarized image of the hole.

IPC Classes  ?

  • G02B 21/00 - Microscopes
  • G02B 26/08 - Optical devices or arrangements using movable or deformable optical elements for controlling the intensity, colour, phase, polarisation or direction of light, e.g. switching, gating or modulating for controlling the direction of light

10.

BEAD-TYPE ADDITIVE MANUFACTURING SYSTEM AND METHOD

      
Application Number 16422356
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Georgeson, Gary E.
  • Kodumuru, Bharath K.
  • Tat, Hong H.
  • Kang, Edward J.
  • Chapdelaine, Nathan J.
  • Maeder, Thomas A.

Abstract

A manufacturing system includes a printhead, at least one profilometer, and a control system. The printhead extrudes a material onto a substrate and forms a new bead during additive manufacturing of an in-work article. The profilometer moves with the printhead and measures an in-work cross-sectional profile of existing beads of the in-work article. The control system generates in-work profile data including the in-work cross-sectional profile at a plurality of in-work profile locations, and continuously compares the in-work profile data to reference profile data of a reference article. The reference profile data includes a reference cross-sectional profile at a plurality of reference profile locations. The control system adjusts, based on the profile comparison, one or more bead forming parameters and causes the printhead to form the new bead according to the bead forming parameters to reduce or prevent nonconformities associated with forming the new bead.

IPC Classes  ?

  • B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
  • 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 50/02 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes
  • B29C 64/118 - Processes of additive manufacturing using only liquids or viscous materials, e.g. depositing a continuous bead of viscous material using filamentary material being melted, e.g. fused deposition modelling [FDM]
  • B29C 64/209 - Heads; Nozzles
  • B22D 23/00 - Casting processes not provided for in groups

11.

TEST FIXTURE FOR ANGLE OF ATTACK (AOA) SENSOR VANE

      
Application Number 16421073
Status Pending
Filing Date 2019-05-23
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Shin, Charley
  • Bang, Bally

Abstract

A test fixture for determining calibration accuracy of an aircraft angle of attack sensor vane includes an outer disc, configured to be transiently fixed to an aircraft exterior portion surrounding the sensor vane, and an inner disc that includes a spring-loaded plunger configured to physically engage the sensor vane during tests. The inner disc is rotatable relative to the outer disc to accommodate rotation of the sensor vane when engaged with the inner disc. The outer disc includes a ring gear fixed thereto; the inner disc includes a manually operated knob containing a spur gear that reacts with the ring gear to rotate the inner disc when the knob is rotated. The outer disc is a clamshell structure formed of an upper annular disc and a lower annular disc rigidly secured together, and the inner disc is rotatably retained between the upper and lower annular discs.

IPC Classes  ?

  • G01P 21/02 - Testing or calibrating of apparatus or devices covered by the other groups of this subclass of speedometers
  • G01P 13/02 - Indicating direction only, e.g. by weather vane
  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • B64D 47/00 - Equipment not otherwise provided for

12.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16416970
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Vijgen, Paul M.
  • Clark, Adam M.
  • Phung, Connie
  • Robinson, Miles Anthony

Abstract

Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine coupled to a nacelle. The multi-segment chine includes a first segment and a second segment. The first segment is oriented along a fore-aft direction. The first segment is rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a plane of the first segment defined by an outer mold line of the first segment. The second segment is fixedly coupled to the nacelle. The second segment is oriented along the fore-aft direction. The second segment is substantially coplanar with the first segment.

IPC Classes  ?

  • B64C 9/36 - Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members the members being fuselages or nacelles
  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
  • B64C 7/02 - Nacelles

13.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16416981
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Konings, Christopher Andrew

Abstract

Aircraft nacelles having adjustable chines are described. An example apparatus includes a first chine rotatably coupled to a nacelle at a first location about an outer circumference of the nacelle. The first chine is rotatable relative to the nacelle about an axis of rotation. The example apparatus further includes a second chine fixedly coupled to the nacelle at a second location about the outer circumference of the nacelle. The second location is circumferentially offset from the first location.

IPC Classes  ?

  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
  • B64D 29/00 - Power-plant nacelles, fairings, or cowlings

14.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16416985
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Goering, Daniel Joseph
  • Clark, Adam M.
  • Phung, Connie
  • Robinson, Miles Anthony
  • Vijgen, Paul M.

Abstract

Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine coupled to a nacelle. The multi-segment chine includes a first segment and a second segment. The first segment is oriented along a fore-aft direction. The first segment is translatable relative to the nacelle along the fore-aft direction. The first segment includes one or more first airflow openings. The second segment is fixedly coupled to the nacelle. The second segment is oriented along the fore-aft direction. The second segment includes one or more second airflow openings. The second segment is substantially coplanar with the first segment. Translation of the first segment adjusts the transverse alignment of the first airflow openings with the second airflow openings to vary an allowable airflow through the multi-segment chine.

IPC Classes  ?

  • B64C 9/36 - Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members the members being fuselages or nacelles
  • B64C 7/02 - Nacelles
  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices

15.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16417104
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Konings, Christopher Andrew
  • Robinson, Miles Anthony

Abstract

Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine coupled to a nacelle. The multi-segment chine includes a first segment oriented along a fore-aft direction. The first segment is translatable relative to the nacelle along the fore-aft direction. The multi-segment chine further includes a second segment oriented along the fore-aft direction. The second segment is substantially coplanar with the first segment.

IPC Classes  ?

  • B64C 9/36 - Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members the members being fuselages or nacelles
  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
  • B64C 7/02 - Nacelles

16.

SHEAR PIN FOR PANEL STRUCTURAL SUPPORT

      
Application Number 16420747
Status Pending
Filing Date 2019-05-23
First Publication Date 2020-11-26
Owner THE BOEING COMPANY (USA)
Inventor Osborne, John C.

Abstract

A shear pin assembly for securing to a face sheet of a honeycomb core sandwich panel structure and to engage a support structure, which includes a head member having a first width dimension and a neck section secured to the head member with the neck section having a second width dimension less than the first width dimension. Further included is a flange secured to the neck section with the flange extending in a direction away from the neck section and a pin member which extends from the flange in a direction away from the head member.

IPC Classes  ?

  • F16B 5/01 - Joining sheets or plates to one another or to strips or bars parallel to them by means of fastening elements specially adapted for honeycomb panels
  • B32B 3/12 - 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 discontinuous layer, i.e. apertured or formed of separate pieces of material characterised by a layer of regularly-arranged cells whether integral or formed individually or by conjunction of separate strips, e.g. honeycomb structure

17.

WIDE FIELD OF VIEW VISUAL DISPLAY SYSTEM IN AN AIRCRAFT FLIGHT SIMULATOR USING FLAT DISPLAY PANELS

      
Application Number 16421835
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Streid, Harry R.

Abstract

A wide field of view visual display system and aircraft flight simulator uses inexpensive, consumer grade flat display panels, such as active matrix organic light-emitting diode display panels. A plurality of the side display panels are arranged in a left side vertical array at a left hand side of the pilot seat of the flight simulator, and in a right side vertical array at a right hand side of the pilot seat. A top edge of a bottom, left side display panel in the left side vertical array and a bottom edge of an upper, left side display panel in the left side vertical array overlap. A top edge of a bottom, right side display panel in the right side vertical array and a bottom edge of an upper, right side display panel in the right side vertical array overlap.

IPC Classes  ?

  • G06F 3/14 - Digital output to display device
  • G09B 9/30 - Simulation of view from aircraft

18.

Thermoplastic Composite Part Manufacturing System and Method

      
Application Number 16992775
Status Pending
Filing Date 2020-08-13
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Steinacher, Philip P.
  • Wilkerson, Randall Dow
  • Fox, James Rodney
  • Matlack, Michael Palmore
  • Merriman, Ryan Joseph
  • Besselsen, Donald C.
  • Bruk, David Phillip

Abstract

A method and apparatus for a continuous compression molding machine. The continuous compression molding machine comprises a tooling die, extending through a heating zone and a cooling zone, a tooling sleeve, and a biasing system. The tooling sleeve corresponds to the tooling die and is for use in forming a thermoplastic composite part from a thermoplastic composite charge when the tooling sleeve with the thermoplastic composite charge is moved with respect to the tooling die through the heating zone and the cooling zone. The biasing system is configured to hold the thermoplastic charge at a first angle within the heating zone and hold the thermoplastic composite charge at a second angle within the cooling zone, as the tooling sleeve moves through the heating zone and the cooling zone with the thermoplastic composite charge. The first angle is different from the second angle.

IPC Classes  ?

  • B29C 43/28 - Compression moulding, i.e. applying external pressure to flow the moulding material; Apparatus therefor of articles of indefinite length incorporating preformed parts or layers, e.g. compression moulding around inserts or for coating articles
  • B29C 43/52 - Heating or cooling
  • B29C 43/44 - Compression means for making articles of indefinite length
  • B29C 43/34 - Feeding the material to the mould or the compression means
  • B29D 99/00 - Subject matter not provided for in other groups of this subclass
  • B29C 70/50 - Shaping or impregnating by compression for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]

19.

DIES FOR FORMING A PART AND ASSOCIATED SYSTEMS AND METHODS

      
Application Number 16422790
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Adducci, Mitchell D.
  • Dummerth, Andrew M.
  • Mckenna, Ashley A.
  • Fennewald, William D.
  • Hill, Iv, Chester

Abstract

Disclosed herein is a die for forming a part. The die comprises a base, comprising a heat-platen interface surface and a part interface surface, and wherein the heat-platen interface surface and the part interface surface are separated by a thickness of the base. The die also comprises inserts, embedded within and circumferentially closed by the base, spaced apart from each other, and extending in a first direction from the heat-platen interface surface toward the part interface surface. The base is made of a first material having a first thermal conductivity. The inserts are made of a second material having a second thermal conductivity. The first thermal conductivity is different than the second thermal conductivity.

IPC Classes  ?

  • B29C 33/38 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor characterised by the material or the manufacturing process
  • B29C 33/42 - SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING - Details thereof or accessories therefor characterised by the shape of the moulding surface, e.g. ribs or grooves

20.

Method and Apparatus for a Software Defined Satellite and Network

      
Application Number 16418053
Status Pending
Filing Date 2019-05-21
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Scott, James P.

Abstract

A software defined network including a constellation of software defined satellites. Each software defined satellite includes computing resources that are dynamically configurable to provide at least one of a plurality of different types of services. Each software defined satellite further includes an interface that interfaces with a software defined network ground station.

IPC Classes  ?

  • H04L 12/24 - Arrangements for maintenance or administration
  • H04L 12/911 - Network admission control and resource allocation, e.g. bandwidth allocation or in-call renegotiation
  • H04B 7/185 - Space-based or airborne stations
  • G06F 9/455 - Emulation; Interpretation; Software simulation, e.g. virtualisation or emulation of application or operating system execution engines

21.

SYSTEM AND METHOD FOR PREHEATING A THERMOPLASTIC CHARGE

      
Application Number 16419320
Status Pending
Filing Date 2019-05-22
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Henson, Landon K.
  • Hull, John

Abstract

A system and method for preheating a thermoplastic charge are disclosed. A gas moving unit establishes a flow of a gas through a conduit. A heating assembly is positioned between an inlet and an outlet of the conduit. A holding vessel is in fluid communication with the conduit and houses a thermoplastic particulate material. The thermoplastic particulate material includes a thermoplastic matrix material. The thermoplastic particulate material is introduced to the flow of the gas to yield a gas-particulate mixture. At least one of the gas and the gas-particulate mixture, moving through the conduit, is heated using the heating assembly to yield a heated gas-particulate mixture. The heated gas-particulate mixture is deposited into a mold from the outlet of the conduit.

IPC Classes  ?

  • B29B 13/02 - Conditioning or physical treatment of the material to be shaped by heating
  • H05B 6/06 - Control, e.g. of temperature, of power
  • H05B 6/10 - Induction heating apparatus, other than furnaces, for specific applications

22.

APPARATUSES AND METHODS FOR APPLYING PRESSURE TO EDGE SURFACES

      
Application Number 16421896
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Howard, Jesse P.

Abstract

An apparatus (100) for applying pressure to at least a portion of an edge surface (192), which bridges opposing faces (194) of a workpiece (190), comprises a frame (110), a first roller (120), a second roller (130), a rotation-control member (140), a first biasing member (150), and a second biasing member (160). The first roller (120) and the second roller (130) are coupled to the frame (110), are rotatable relative to the frame (110) about a first pivot axis (125), and are translationally fixed relative to the frame (110). The rotation-control member (140) is coupled to and is movable relative to the frame (110), controlling rotation of the first roller (120) and the second roller (130) relative to the frame (110). The first biasing member (150) is coupled to the first roller (120) and to the second roller (130) and is configured to operate in tension. The second biasing member (160) is positioned, in compression, between the frame (110) and the rotation-control member (140).

IPC Classes  ?

  • B30B 3/04 - Presses characterised by the use of rotary pressing members, e.g. rollers, rings, discs co-operating with one another, e.g. with co-operating cones
  • B30B 9/28 - Presses specially adapted for particular purposes for forming shaped articles
  • B30B 9/24 - Presses specially adapted for particular purposes for squeezing-out liquid from liquid-containing material, e.g. juice from fruits, oil from oil-containing material using an endless pressing band

23.

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

      
Application Number 16417475
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
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 11/00 - Connecting constructional elements or machine parts by sticking or pressing them together, e.g. cold pressure welding
  • B29C 70/86 - Incorporating in coherent impregnated reinforcing layers

24.

APPARATUSES AND METHODS FOR APPLYING PRESSURE TO EDGE SURFACES

      
Application Number 16421919
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Howard, Jesse P.

Abstract

An apparatus (100) for applying pressure to at least a portion of an edge surface (192), which bridges opposing faces (194) of a workpiece (190), comprises a frame (110), a first roller (120), a second roller (130), a rotation-control member (140), a first biasing member (150), and a second biasing member (160). The first roller (120) and the second roller (130) are coupled to the frame (110), are rotatable relative to the frame (110), and are translationally fixed relative to the frame (110). The rotation-control member (140) is movable relative to the frame (110), controlling rotation of the first roller (120) and the second roller (130) relative to the frame (110). The first biasing member (150) is configured to operate in compression along a second axis (102). The second biasing member (160) is positioned, in compression, between the frame (110) and the rotation-control member (140).

IPC Classes  ?

  • B30B 3/04 - Presses characterised by the use of rotary pressing members, e.g. rollers, rings, discs co-operating with one another, e.g. with co-operating cones
  • B30B 9/28 - Presses specially adapted for particular purposes for forming shaped articles
  • B30B 9/24 - Presses specially adapted for particular purposes for squeezing-out liquid from liquid-containing material, e.g. juice from fruits, oil from oil-containing material using an endless pressing band
  • B30B 11/00 - Presses specially adapted for forming shaped articles from material in particulate or plastic state, e.g. briquetting presses or tabletting presses

25.

TRANSFORMER AND METHOD OF GENERATING MULTIPLE MULTIPHASE OUTPUT SIGNALS

      
Application Number 16417204
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner THE BOEING COMPANY (USA)
Inventor Huang, Jian

Abstract

An apparatus includes a plurality of input nodes configured to receive a multiphase alternating current (AC) input signal. The apparatus further includes a plurality of inductors, a neutral terminal, a first plurality of output nodes, and a second plurality of output nodes. The plurality of inductors is coupled to the plurality of input nodes, and the neutral terminal is coupled to the plurality of inductors. The first plurality of output nodes is coupled to the plurality of inductors and is configured to output a first multiphase AC output signal. The second plurality of output nodes is coupled to the plurality of inductors and is configured to output a second multiphase AC output signal.

IPC Classes  ?

  • H01F 30/12 - Two-phase, three-phase or polyphase transformers
  • H02M 7/53 - Conversion of dc power input into ac power output without possibility of reversal by static converters using discharge tubes with control electrode or semiconductor devices with control electrode using devices of a triode or transistor type requiring continuous application of a control signal

26.

SYSTEM AND METHOD FOR CO-REGISTERING TERRAIN DATA AND IMAGE DATA

      
Application Number 16421305
Status Pending
Filing Date 2019-05-23
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Klein, Robert J.

Abstract

A method for co-registering terrain data and image data includes receiving terrain data and image data. The method also includes determining a position of a light source based upon the image data. The method also includes creating a hillshade representation of the terrain data based upon the terrain data and the position of the light source. The method also includes identifying a portion of the hillshade representation and a portion of the image data that correspond to one another. The method also includes comparing the portion of the hillshade representation and the portion of the image data. The method also includes determining a vector control between the portion of the hillshade representation and the portion of the image data based upon the comparison. The method also includes applying the vector control to the image data to produce updated image data.

IPC Classes  ?

  • G06K 9/00 - Methods or arrangements for reading or recognising printed or written characters or for recognising patterns, e.g. fingerprints
  • G06K 9/62 - Methods or arrangements for recognition using electronic means

27.

ADDITIVE MANUFACTURING WITH ADJUSTED COOLING RESPONSIVE TO THERMAL CHARACTERISTIC OF WORKPIECE

      
Application Number 16421303
Status Pending
Filing Date 2019-05-23
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Baker, Andrew H.
  • Castle, James B.
  • Thomas, Eric Erwin
  • Easley, Samuel Joseph

Abstract

A method for use in additive manufacturing of a three-dimensional workpiece is described. The method includes depositing material onto a substrate to form a shape of the workpiece in accordance with an additive manufacturing process; determining a thermal characteristic of at least a portion of the workpiece during the additive manufacturing process; determining that the thermal characteristic of at least the portion exceeds a threshold associated with the portion; adjusting a cooling parameter of a cooling flow to be applied to the workpiece responsive to determining that the thermal characteristic of at least the portion exceeds the threshold associated with the portion; and applying the cooling flow with the adjusted cooling parameter to at least the portion of the workpiece.

IPC Classes  ?

  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B29C 64/153 - Processes of additive manufacturing using only solid materials using layers of powder being selectively joined, e.g. by selective laser sintering or melting
  • B29C 64/268 - Arrangements for irradiation using electron beams [EB]
  • B29C 64/364 - Conditioning of environment
  • B29C 64/393 - Data acquisition or data processing for additive manufacturing for controlling or regulating additive manufacturing processes

28.

SUPPORTING OFF-WING MAINTENANCE OF AN ENGINE OF AN AIRCRAFT

      
Application Number 16417065
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner THE BOEING COMPANY (USA)
Inventor Rice, Joseph

Abstract

A method of supporting off-wing maintenance of an engine of a specific aircraft includes accessing flight data for a plurality of aircraft including measurements of properties from sensors or avionic systems, and maintenance data that indicates past maintenance or off-wing maintenance of a corresponding engine of each aircraft. A machine learning model is built to predict a life expectancy of the engine of the specific aircraft, measured to future off-wing maintenance of the engine, using a machine learning algorithm, and a set of features produced from selected properties. The machine learning model is built further using a training set produced from the set of features, the flight data including measurements of the selected properties, and the maintenance data. The machine learning model is then output for deployment to predict and thereby produce a prediction of the life expectancy of the engine of the specific aircraft from distinct flight data.

IPC Classes  ?

  • B64F 5/60 - Testing or inspecting aircraft components or systems
  • G06N 20/00 - Machine learning
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for

29.

MALWARE DETECTION WITH DYNAMIC OPERATING-SYSTEM-LEVEL CONTAINERIZATION

      
Application Number 16418394
Status Pending
Filing Date 2019-05-21
First Publication Date 2020-11-26
Owner THE BOEING COMPANY (USA)
Inventor Thakkar, Rahul C.

Abstract

A method of protecting a computer from malicious software includes receiving a computer file, and scanning, via anti-malware, the computer file for known malicious software. The method include, when the anti-malware fails to detect known malicious software in the computer file, performing a dynamic operating-system-level containerization to access content of the computer file, including creating and launching an isolated container on the computer. The method includes accessing the content of the computer file in the isolated container on the computer, and monitoring execution of computer-readable program code in the isolated container as the content of the computer file is accessed. And the method includes performing a remedial action when as the execution of computer-readable program code in the isolated container is monitored, a pattern in the execution is detected that indicates the computer file contains malicious software that is otherwise unknown.

IPC Classes  ?

  • G06F 21/56 - Computer malware detection or handling, e.g. anti-virus arrangements

30.

COMPOSITE STRUCTURE FABRICATION SYSTEMS AND METHODS

      
Application Number 16991933
Status Pending
Filing Date 2020-08-12
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Encinosa, Jose L.
  • Zambrana, Samuel F.
  • Rotter, Daniel M.
  • Chapman, Michael Robert
  • Halladin, Stephen K.
  • Lee, Benjamin Bowen
  • Little, Joshua Dee
  • Mccarville, Douglas Alan
  • Medenciy, Jason A.
  • Chiupka, Russell D.
  • Rabiega, Marcin Artur
  • Yurchik, Andrey F.
  • Hansen, Martin W.
  • Harper, Thomas P.

Abstract

Composite structure fabrication systems and methods. The systems include a plurality of ply carriers, each of which is configured to support at least one ply segment, and an elongate forming mandrel, which defines an elongate ply forming surface that is shaped to define a surface contour of the composite structure. The systems further include a carrier transfer device, which is configured to selectively convey a selected ply carrier from a ply kitting area to an intermediate location, and a forming machine, which is configured to deform the selected ply carrier and a respective ply segment over a selected portion of the elongate ply forming surface. The forming machine further is configured to separate the selected ply carrier from the respective ply segment and return the selected ply carrier to the carrier transfer device. The methods include methods of operating the systems.

IPC Classes  ?

  • 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
  • B29C 70/38 - Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
  • B29C 31/08 - Feeding, e.g. into a mould cavity of preforms
  • B29C 65/02 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure

31.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16417039
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Philipp, Paul Brian
  • Konings, Christopher Andrew

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 9/36 - Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members the members being fuselages or nacelles
  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
  • B64C 7/02 - Nacelles

32.

ACTUATOR-BASED COMPENSATION FOR DEFORMATION OF A MANDREL

      
Application Number 16419190
Status Pending
Filing Date 2019-05-22
First Publication Date 2020-11-26
Owner THE BOEING COMPANY (USA)
Inventor
  • Kimball, Nicklaus Cummings
  • Mcnulty, Michael John
  • Loftus, Robert

Abstract

A system to manufacture an object includes a headstock, a tailstock, and a mandrel having a first end coupled to the headstock and a second end coupled to the tailstock. The system also includes an actuator coupled to one or more of the headstock, the tailstock, or the mandrel, the actuator operable to apply a force to the one or more of the headstock, the tailstock, or the mandrel, to oppose deformation of the mandrel.

IPC Classes  ?

  • B21D 22/16 - Spinning over shaping mandrels or formers
  • B29C 70/32 - 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 on a rotating mould, former or core

33.

CONFORMABLE APPARATUS, SYSTEMS AND METHODS FOR TREATING A COMPOSITE MATERIAL

      
Application Number 16419178
Status Pending
Filing Date 2019-05-22
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Mccowin, Peter D.

Abstract

A conformable apparatus for treating a composite material. The conformable apparatus includes a contact layer that is conformable and includes a plurality of contact elements. Each contact element of the plurality of contact elements includes a first major side, a second major side opposed from said first major side, and at least one side surface extending between said first major side and said second major side. The contact layer further includes a contact surface at least partially defined by the first major sides of the plurality of contact elements and a backing surface at least partially defined by the second major sides of said plurality of contact elements. The conformable apparatus also includes a backing layer positioned against said backing surface of said contact layer.

IPC Classes  ?

  • B29C 43/36 - Moulds for making articles of definite length, i.e. discrete articles
  • B29C 70/42 - Shaping or impregnating by compression for producing articles of definite length, i.e. discrete articles

34.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16416960
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Dodt, Thomas K.
  • Clark, Adam M.

Abstract

Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine having a first segment and a second segment. The first segment is fixedly coupled to a nacelle. The second segment is rotatable relative to the first segment about an axis of rotation. The axis of rotation is substantially perpendicular to a local area of an outer surface of the nacelle.

IPC Classes  ?

  • B64C 9/36 - Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members the members being fuselages or nacelles
  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
  • B64C 7/02 - Nacelles

35.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16416973
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Konings, Christopher Andrew
  • Phung, Connie
  • Goering, Daniel Joseph
  • Philipp, Paul Brian

Abstract

Aircraft nacelles having adjustable chines are described. An example apparatus includes a chine rotatably coupled to a nacelle. The chine is rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a local area of an outer surface of the nacelle.

IPC Classes  ?

  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
  • B64D 29/00 - Power-plant nacelles, fairings, or cowlings

36.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16416990
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Konings, Christopher Andrew

Abstract

Aircraft nacelles having adjustable chines are described. An example apparatus includes a multi-segment chine rotatably coupled to a nacelle. The multi-segment chine includes at least two segments. The at least two segments include a first segment and a second segment. The first segment and the second segment are independently rotatable relative to the nacelle about an axis of rotation.

IPC Classes  ?

  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
  • B64D 29/00 - Power-plant nacelles, fairings, or cowlings

37.

FASTENER-COATING TOOLS, KITS THEREOF, AND RELATED METHODS

      
Application Number 16418674
Status Pending
Filing Date 2019-05-21
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Hopkins, Richard Lynn
  • Ducworth, Lyman Scott
  • Larrabee, Diana Dujunco Dan
  • Jackson, Janet Karen H.
  • Boyd, Sandra Loraine
  • Vasquez, Elker I.

Abstract

Fastener-coating tools (100), kits (200) thereof, and methods (300) of coating a fastener assembly (50) are disclosed. Fastener-coating tools (100) comprise a non-permeable body (102) and a permeable body (112) that laps over at least a portion of an outer surface (110) of the non-permeable body (102), laps over all of a terminal surface (116) of the non-permeable body (102), laps over at least a portion of an inner surface (108) of the non-permeable body (102), spans an internal cavity (106) of the non-permeable body (102), and defines a fastener cavity (114) that is sized and shaped to receive a portion of a fastener assembly (50) to be coated.

IPC Classes  ?

  • B05C 1/02 - Apparatus in which liquid or other fluent material is applied to the surface of the work by contact with a member carrying the liquid or other fluent material, e.g. a porous member loaded with a liquid to be applied as a coating for applying liquid or other fluent material to separate articles
  • B05D 1/28 - Processes for applying liquids or other fluent materials performed by transfer from the surfaces of elements carrying the liquid or other fluent material, e.g. brushes, pads, rollers

38.

ADDITIVELY MANUFACTURED RADIO FREQUENCY FILTER

      
Application Number 16422939
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Aston, Richard W.
  • Hastings, Nicole M.
  • Schoenborn, Nicole Diane

Abstract

A radio frequency filter apparatus is disclosed, including an elongate hollow body portion having an inner side and an outer side. The apparatus further includes an iris structure on the inner side of the body portion and a stiffening structure on the outer side of the body portion. The stiffening structure is aligned with the iris structure.

IPC Classes  ?

  • H01P 1/207 - Hollow waveguide filters
  • H01P 11/00 - Apparatus or processes specially adapted for manufacturing waveguides or resonators, lines, or other devices of the waveguide type
  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B22F 5/10 - Manufacture of workpieces or articles from metallic powder characterised by the special shape of the product of articles with cavities or holes, not otherwise provided for in the preceding subgroups

39.

Surface Area of Fixtures

      
Application Number 16989580
Status Pending
Filing Date 2020-08-10
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor Visnoski, Bryan J.

Abstract

A method and apparatus. The apparatus comprises a first portion of a tool and a second portion of the tool. The first portion of the tool has a first surface. The first surface has a shape that is complementary to a first portion of a part. The second portion has at least one of a second surface configured to be recessed from a second portion of the part or a hollow portion.

IPC Classes  ?

  • B23Q 3/08 - Work-clamping means other than mechanically-actuated
  • B23C 9/00 - MILLING - Details or accessories so far as specially adapted to milling machines or cutters
  • B23Q 3/06 - Work-clamping means
  • B25B 11/00 - Work holders or positioners not covered by groups , e.g. magnetic work holders, vacuum work holders
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor

40.

AIRCRAFT LANDING GEAR ASSEMBLIES, AIRCRAFT INCLUDING THE LANDING GEAR ASSEMBLIES, AND METHODS OF DEPLOYING THE LANDING GEAR ASSEMBLIES

      
Application Number 16419548
Status Pending
Filing Date 2019-05-22
First Publication Date 2020-11-26
Owner THE BOEING COMPANY (USA)
Inventor Jackson, Rick A.

Abstract

Aircraft landing gear assemblies, aircraft including the landing gear assemblies, and methods of deploying landing gear assemblies. The landing gear assemblies include an elongate landing gear strut, a wheel assembly, and a deployment structure. The elongate landing gear strut includes a first strut end region, an opposed second strut end region, and a wheel assembly mount. The wheel assembly is coupled to the wheel assembly mount. The deployment structure is configured to selectively transition the landing gear assembly between a stowed state and a deployed state.

IPC Classes  ?

  • B64C 25/40 - Alighting gear characterised by elements which contact the ground or similar surface the elements being rotated before touch-down
  • B64C 25/26 - Control or locking systems therefor
  • B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies

41.

Digital Controlled Reception Pattern Antenna for Satellite Navigation

      
Application Number 16420529
Status Pending
Filing Date 2019-05-23
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Murphy, Timothy Allen
  • Harris, William Matthew

Abstract

A satellite navigation system including a digital controlled reception pattern antenna (DCRPA) subsystem and a global navigation satellite system (GNSS) receiver. The overall system is designed so that all radio frequency (RF) processing and digital sampling are incorporated in the DCRPA subsystem. The RF signal from each element of the DCRPA array is digitized separately. Then the resultant digital samples are combined into a single bit stream which is transmitted to the GNSS receiver. Preferably the GNSS receiver is a software defined radio. The arrangement allows the DCRPA subsystem and the GNSS receiver to be connected with a single coaxial cable. Such an arrangement would allow simple retrofit of CRPA antennas to existing airframe designs as well as simple and inexpensive installations on new aircraft designs.

IPC Classes  ?

  • G01S 19/21 - Interference related issues
  • G01S 19/37 - Hardware or software details of the signal processing chain
  • G01S 19/24 - Acquisition or tracking of signals transmitted by the system
  • G01S 19/30 - Acquisition or tracking of signals transmitted by the system code related

42.

ADDITIVELY MANUFACTURED MESH CAVITY ANTENNA

      
Application Number 16422949
Status Pending
Filing Date 2019-05-24
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Aston, Richard W.
  • Hastings, Nicole M.
  • Sanghvi, Manav H.
  • Bieti, Martin W.
  • Schoenborn, Nicole Diane

Abstract

An antenna device is disclosed, including a cavity structure having a floor portion and a perimeter wall portion connected to the floor portion. A dipole structure extends upward from a center region of the floor portion inside the cavity structure. At least one of the wall portion and the dipole structure has an opening small enough relative to an expected radio frequency wavelength to avoid affecting antenna performance.

IPC Classes  ?

  • H01Q 1/42 - Housings not intimately mechanically associated with radiating elements, e.g. radome
  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • B33Y 10/00 - Processes of additive manufacturing
  • B33Y 80/00 - Products made by additive manufacturing
  • H01Q 9/16 - Resonant antennas with feed intermediate between the extremities of the antenna, e.g. centre-fed dipole

43.

MULTI-COMPONENT MELT ELECTROMAGNETIC EFFECT PROTECTION CAP SYSTEM

      
Application Number 16420948
Status Pending
Filing Date 2019-05-23
First Publication Date 2020-11-26
Owner THE BOEING COMPANY (USA)
Inventor
  • Auffinger, Sean
  • Riley, Terrell

Abstract

A protection cap assembly for enclosing an end portion of a fastener which extends through a structure of an aircraft includes a cap member having a sidewall defining an opening and an interior space wherein the opening is aligned with the interior space for receiving the end portion of the fastener through the opening and into the interior space and an end surface for abutting the structure. The protection cap assembly further includes a projection secured to and which extends from the end surface of the sidewall of the cap member.

IPC Classes  ?

  • F16B 37/14 - Cap nuts; Nut caps or bolt caps
  • F16B 33/00 - Features common to bolt and nut
  • B29C 65/08 - Joining of preformed parts; Apparatus therefor by heating, with or without pressure using ultrasonic vibrations

44.

AIRCRAFT NACELLES HAVING ADJUSTABLE CHINES

      
Application Number 16417136
Status Pending
Filing Date 2019-05-20
First Publication Date 2020-11-26
Owner The Boeing Company (USA)
Inventor
  • Philipp, Paul Brian
  • Bays-Muchmore, C. Byram
  • Goering, Daniel Joseph

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 rotatable relative to the nacelle about an axis of rotation. The axis of rotation is substantially perpendicular to a plane of the chine defined by an outer mold line of the chine.

IPC Classes  ?

  • B64D 29/06 - Attaching of nacelles, fairings, or cowlings
  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices

45.

Input coupler for chip-scale laser receiver device

      
Application Number 16656628
Grant Number 10845550
Status In Force
Filing Date 2019-10-18
First Publication Date 2020-11-24
Grant Date 2020-11-24
Owner THE BOEING COMPANY (USA)
Inventor
  • Efimov, Oleg M.
  • Huang, Biqin
  • Patterson, Pamela R.
  • Sarkissian, Raymond
  • Sayyah, Keyvan

Abstract

A laser receiver device and an associated input coupler are provided. In this regard, a chip-scale laser receiver device is provided that includes an input coupler that is configured to receive a gaussian beam. The input coupler includes a first waveguide having an optically-transparent material and a second waveguide coupled to the first waveguide. The second waveguide has a tapered configuration that tapers to a predetermined width across a length of not less than 500 micrometers. The input coupler further includes a third waveguide coupled to the second waveguide. The third waveguide has a tapered configuration that tapers to a predetermined width across a length of not less than 250 micrometers. The chip-scale laser receiver device further includes a bus optical waveguide coupled to receive a signal output from the input coupler, and to output a wavelength-multiplexed laser signal.

IPC Classes  ?

  • G02B 6/42 - Coupling light guides with opto-electronic elements
  • G02B 6/293 - Optical coupling means having data bus means, i.e. plural waveguides interconnected and providing an inherently bidirectional system by mixing and splitting signals with wavelength selective means
  • H04B 10/50 - Transmitters
  • H04B 10/67 - Optical arrangements in the receiver
  • H04J 14/02 - Wavelength-division multiplex systems
  • H04B 10/25 - Arrangements specific to fibre transmission

46.

Hydraulic manifold for semi-levered gear actuator

      
Application Number 29689251
Grant Number D0902969
Status In Force
Filing Date 2019-04-29
First Publication Date 2020-11-24
Grant Date 2020-11-24
Owner THE BOEING COMPANY (USA)
Inventor Mellor, Mitchell L. R.

47.

Aircraft to ground data systems and computing methods

      
Application Number 16721510
Grant Number 10848939
Status In Force
Filing Date 2019-12-19
First Publication Date 2020-11-24
Grant Date 2020-11-24
Owner The Boeing Company (USA)
Inventor
  • Panergo, Reynold Rullan
  • Puttaswamy, Lakshmi M.
  • Mattox, Mycah
  • Natarajan, Subramaniam
  • Santharam, Selvakumar
  • Anstey, Timothy William
  • Vanrheenen, Nathan T.

Abstract

A computing method for exchanging data between an aircraft computing device and a ground computing device comprises receiving an initial communication from an aircraft service executing on the aircraft computing device located onboard an aircraft; determining an aircraft classifier associated with the aircraft; selecting an aircraft API for communicating with the aircraft service; transmitting one or more first communications to the ground computing device; and transmitting one or more second communications to the aircraft service, wherein the one or more first communications and the one or more second communications cause a data file to be exchanged between the ground computing device and the aircraft computing device.

IPC Classes  ?

  • H04W 4/42 - Services specially adapted for particular environments, situations or purposes for vehicles, e.g. vehicle-to-pedestrians [V2P] for mass transport vehicles, e.g. buses, trains or aircraft
  • H04L 29/08 - Transmission control procedure, e.g. data link level control procedure
  • G08G 5/00 - Traffic control systems for aircraft

48.

System and method of tracking entry to and exit from a confined space

      
Application Number 16670195
Grant Number 10848921
Status In Force
Filing Date 2019-10-31
First Publication Date 2020-11-24
Grant Date 2020-11-24
Owner The Boeing Company (USA)
Inventor
  • Mcinnis, Michael D.
  • Salour, Ali
  • Pang, David S.
  • Salstrom, Daren

Abstract

A method of tracking entry to and exit from a confined space includes a portable radio beacon placed proximate to but outside the confined space transmitting a first radio signal with an identifier that is associated with the confined space. A mobile device receives the first radio signal, measures a first real-time value of a first measure of received signal strength or quality, and transmits a second radio signal with the identifier and the first real-time value. A base station receives the second radio signal, measures a second real-time value of a second measure of received signal strength or quality, and transmits data including the identifier, and the first and second real-time values. A computer receives the data, determines proximity of the mobile device to the confined space from the identifier, and determines whether the mobile device is outside or inside the confined space from the real-time values.

IPC Classes  ?

  • H04W 4/029 - Location-based management or tracking services
  • H04W 4/021 - Services related to particular areas, e.g. point of interest [POI] services, venue services or geofences
  • H04B 17/309 - Measuring or estimating channel quality parameters

49.

Polymer with upper critical solution temperature

      
Application Number 16867955
Status Pending
Filing Date 2020-05-06
First Publication Date 2020-11-19
Owner THE BOEING COMPANY (USA)
Inventor
  • Monteiro, Michael
  • Hossain, Daloar

Abstract

Aspects generally relate to a temperature responsive polymer, more specifically to a polymer exhibiting an upper critical solution temperature (UCST) in an aqueous solution. In one aspect, a monomer compound includes one or more amide or thioamide groups; one or more ureido or thioureido groups; and one or more ethylenically unsaturated groups. In one aspect, a polymer, such as a homopolymer or a copolymer, is produced by polymerization of the monomer compound. The copolymer is produced by polymerization of the monomer compound and a comonomer, such as a hydrophobic comonomer, a hydrophilic comonomer, a pH responsive comonomer, a light responsive comonomer, and combinations thereof. The polymer exhibits a UCST from about 1° C. to about 100° C. in an aqueous solution at 1 atm.

IPC Classes  ?

  • C07C 275/14 - Derivatives of urea, i.e. compounds containing any of the groups the nitrogen atoms not being part of nitro or nitroso groups having nitrogen atoms of urea groups bound to acyclic carbon atoms of an acyclic and saturated carbon skeleton being further substituted by nitrogen atoms not being part of nitro or nitroso groups
  • C08F 220/18 - Esters of monohydric alcohols or phenols of phenols or of alcohols containing two or more carbon atoms with acrylic or methacrylic acids
  • C08F 220/36 - Esters containing nitrogen containing oxygen in addition to the carboxy oxygen
  • C08F 120/36 - Esters containing nitrogen containing oxygen in addition to the carboxy oxygen
  • C07C 273/18 - Preparation of urea or its derivatives, i.e. compounds containing any of the groups the nitrogen atoms not being part of nitro or nitroso groups of substituted ureas

50.

ZERO MASK FIXTURES FOR PARTS

      
Application Number 16983490
Status Pending
Filing Date 2020-08-03
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Shinozaki, John
  • Chungbin, Jerry Deming
  • Wu, Steven Kuan-Chi

Abstract

Systems and methods are provided for securement of parts. One embodiment is a method for securing a part during fabrication. The method includes forming an interference fit between a pin and a wall defining a hole, supporting a weight of the part with the interference fit, and rotating the part around an axis of the part while the weight of the part is supported.

IPC Classes  ?

  • B05B 13/02 - Means for supporting work; Arrangement or mounting of spray heads; Adaptation or arrangement of means for feeding work
  • B05B 16/00 - Spray booths

51.

In-Service Maintenance Process Using Unmanned Aerial Vehicles

      
Application Number 16410085
Status Pending
Filing Date 2019-05-13
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor Georgeson, Gary E.

Abstract

Methods for performing repair operations using one or more unmanned aerial vehicles (UAVs). First, an unmanned aerial vehicle equipped with a camera is flown to a position in a vicinity of an area of interest on a surface of a structure. Image data representing one or more images of the structure in the area is acquired using the camera. Second, an unmanned aerial vehicle equipped with a non-destructive examination (NDE) sensor unit is flown until the NDE sensor unit is within measurement range of the structure in the area of interest. Then NDE sensor data representing structural characteristics of the structure in the area of interest is acquired. Third, an unmanned aerial vehicle equipped with a repair tool is moved to a location that places the repair tool in contact with the surface in the area of interest. Then the structure in the area is repaired using the repair tool. Once the repair has been completed, a UAV equipped with a camera or an NDE sensor unit may be used to determine whether the repaired structure should be placed back in service or not.

IPC Classes  ?

  • G05D 1/10 - Simultaneous control of position or course in three dimensions
  • B23P 6/00 - Restoring or reconditioning objects
  • G05D 1/00 - Control of position, course, altitude, or attitude of land, water, air, or space vehicles, e.g. automatic pilot
  • B64C 39/02 - Aircraft not otherwise provided for characterised by special use
  • B64D 47/08 - Arrangements of cameras

52.

SYSTEM FOR DETERMINING THE STACK CLOSURE PRESSURE OF A BRAKE STACK

      
Application Number 16410720
Status Pending
Filing Date 2019-05-13
First Publication Date 2020-11-19
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  ?

  • F16K 31/04 - Operating means; Releasing devices magnetic using a motor
  • H02K 49/10 - Dynamo-electric clutches; Dynamo-electric brakes of the permanent-magnet type

53.

AUTOCLAVE PLENUM

      
Application Number 16410957
Status Pending
Filing Date 2019-05-13
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Nelson, Karl M.
  • Wu, Tateh

Abstract

An autoclave comprises an elongate chamber enclosing an interior atmosphere, a floor configured to support one or more objects, and a plenum extending through a portion of the elongate chamber. The plenum includes an inlet as well as a plurality of outlets. The inlet is configured to receive a plenum flow of the interior atmosphere, while each of the plurality of outlets is configured to release a portion of the plenum flow to a different locus of the elongate chamber.

IPC Classes  ?

  • B01J 3/02 - Feed or outlet devices therefor
  • B01J 3/04 - Pressure vessels, e.g. autoclaves

54.

Method and Apparatus for Remote Angle Calibration and Measurement

      
Application Number 16414128
Status Pending
Filing Date 2019-05-16
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Englund, Norman
  • Yeeles, Christopher
  • Ng, Kim
  • Fortier, James
  • Rugland, Paul

Abstract

Methods and devices to measure an angular deflection of an aircraft member. The devices are configured to be attached to the aircraft member. The devices are configured to obtain an orientation of the device about three separate axes. The methods use initial orientation values and dynamic orientation values to calculate an axis of rotation. Using the axis of rotation, the deflection angle can be calculated for the aircraft member.

IPC Classes  ?

  • B64C 9/12 - Adjustable control surfaces or members, e.g. rudders surfaces of different type or function being simultaneously adjusted
  • B64C 9/34 - Adjustable control surfaces or members, e.g. rudders collapsing or retracting against or within other surfaces or other members
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for
  • G06F 17/11 - Complex mathematical operations for solving equations

55.

AEROSEAL AND METHOD OF FORMING THE SAME

      
Application Number 16414938
Status Pending
Filing Date 2019-05-17
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Gruner, Bryan J.
  • Dahl, Bruce A.

Abstract

An aeroseal comprises a substantially straight portion having a first engagement end and a second engagement end opposite the first engagement end. The aeroseal also comprises a first engagement extension extending transversely from the first engagement end of the substantially straight portion and having a distal end. The aeroseal further comprises a second engagement extension extending transversely from the second engagement end of the substantially straight portion and having a distal end. The aeroseal also comprises a substantially curved portion interconnecting the distal end of the first engagement extension and the distal end of the second engagement extension to form an acute angle between the first and second engagement extensions and facing away from the substantially straight portion.

IPC Classes  ?

  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
  • B64C 3/36 - Structures adapted to reduce effects of aerodynamic or other external heating

56.

METHOD TO RE-LOFT A REDESIGNED JET ENGINE PRIMARY EXHAUST NOZZLE FOR AN EXISTING AIRPLANE TO PROVIDE CLEARANCE TO AIRCRAFT HEAT SHIELD STRUCTURE TO PREVENT CONTACT, FRACTURE, AND LIBERATION OF PORTIONS OF THE NOZZLE WHICH MIGHT CAUSE HAZARD TO CONTINUED SAFE FLIGHT

      
Application Number 16415310
Status Pending
Filing Date 2019-05-17
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor Bender, Norman Harold

Abstract

A nozzle having a forward portion skewed downwards and an aft portion translated downwards provides sufficient clearance between the nozzle and the heat shield structure to prevent contact in the event of large deflections (e.g., as associated with a fan blade Out (FBO) condition). Such large deflections must be accounted for to meet federal aviation regulations and gain airplane CFR 14 Part 25 Certification.

IPC Classes  ?

  • F02K 1/82 - Jet pipe walls, e.g. liners
  • B64D 33/04 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes

57.

Electrical Stimulation System

      
Application Number 16415788
Status Pending
Filing Date 2019-05-17
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Laughlin, Brian Dale
  • Laughlin, Dane Brian
  • Laughlin, Madison Lauryn

Abstract

A method, apparatus, and system for delivering an electrical current. Optical signals are sent through a group of optical fibers in a medium. Response optical signals occurring in response to the optical signals sent through the group of optical fibers are detected when the group of optical fibers is located in the medium. A group of parameters for the medium is determined using the response optical signals. A group of electrical currents is sent through a group of electrodes based on the group of parameters, wherein the group of electrodes emit the group of electrical currents.

IPC Classes  ?

  • A61N 1/05 - Electrodes for implantation or insertion into the body, e.g. heart electrode
  • A61N 1/36 - Applying electric currents by contact electrodes alternating or intermittent currents for stimulation, e.g. heart pace-makers

58.

BERTHING SYSTEM FOR SPACECRAFT

      
Application Number 16416078
Status Pending
Filing Date 2019-05-17
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Dharmaraj, Raju
  • Hoffman, Thomas L.

Abstract

Berthing systems for visiting spacecraft and associated methods. In one embodiment, a berthing system includes a tunnel having an interface surface that defines a hard capture mating plane for mating with a docking system of a target spacecraft. The berthing system further includes hooks disposed circumferentially on the interface surface, one or more pressure seals disposed on the interface surface, spring-loaded guide petals spaced around an inner peripheral surface of the tunnel that are configured to independently slide in the axial direction, and capture latches spaced around the inner peripheral surface that are configured to engage mechanical latch strikers on the docking system.

IPC Classes  ?

  • B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
  • F16B 7/04 - Clamping or clipping connections

59.

NON-SEALING BERTHING SYSTEM FOR SPACECRAFT

      
Application Number 16416100
Status Pending
Filing Date 2019-05-17
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Dharmaraj, Raju
  • Hoffman, Thomas L.

Abstract

Berthing systems for visiting spacecraft and associated methods. In one embodiment, a non-sealing berthing system includes a tunnel having an interface surface that mates with a docking system of a target spacecraft. The berthing system further includes sliding hooks disposed circumferentially on the interface surface of the tunnel, preload members disposed circumferentially at the interface surface of the tunnel and configured to extend and retract from the interface surface in an axial direction, guide petals spaced around an inner peripheral surface of the tunnel, and soft capture petals spaced around the inner peripheral surface of the tunnel. The soft capture petals include capture latches configured to engage mechanical latch strikers on the docking system of the target spacecraft.

IPC Classes  ?

  • B64G 1/64 - Systems for coupling or separating cosmonautic vehicles or parts thereof, e.g. docking arrangements
  • F16B 7/04 - Clamping or clipping connections

60.

SPHERICAL MECHANISM ROBOT ASSEMBLY, SYSTEM, AND METHOD FOR ACCESSING A CONFINED SPACE IN A VEHICLE TO PERFORM CONFINED SPACE OPERATIONS

      
Application Number 16416145
Status Pending
Filing Date 2019-05-17
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor Gunther, Scott W.

Abstract

There is provided a spherical mechanism robot assembly for accessing a confined space in a vehicle, to perform confined space operation(s) in the vehicle. The assembly includes a base structure configured for attachment to the vehicle. The assembly includes a spherical mechanism structure having a first end attached to the base structure, and having a second end. The spherical mechanism structure includes a plurality of mechanical links, joints coupling the plurality of mechanical links together, and a plurality of actuators having one or more actuators coupled at each joint of the plurality of joints. The assembly includes an end effector attached to the second end of the spherical mechanism structure. The assembly is configured such that a majority portion remains outside of the confined space, while a remaining portion of the assembly accesses and occupies the confined space in the vehicle, to perform the confined space operation(s) in the vehicle.

IPC Classes  ?

61.

METHOD AND SYSTEM FOR FABRICATING AN ELECTRICAL CONDUCTOR ON A SUBSTRATE

      
Application Number 16409999
Status Pending
Filing Date 2019-05-13
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Braley, Daniel J.
  • Wilson, Peter A.

Abstract

A method for fabricating an electrical conductor on a substrate by cold spraying includes propelling a solid powder composition that includes copper and highly oriented pyrolytic graphite using a gas propellant, and directing the solid powder composition towards the substrate at a velocity sufficient to cause the solid powder composition to undergo plastic deformation and to adhere to the substrate to deposit the electrical conductor thereon.

IPC Classes  ?

  • C23C 24/04 - Impact or kinetic deposition of particles
  • H01B 13/00 - Apparatus or processes specially adapted for manufacturing conductors or cables
  • H01B 1/04 - Conductors or conductive bodies characterised by the conductive materials; Selection of materials as conductors mainly consisting of carbon-silicon compounds, carbon, or silicon
  • H01B 1/02 - Conductors or conductive bodies characterised by the conductive materials; Selection of materials as conductors mainly consisting of metals or alloys

62.

SYSTEM FOR DETERMINING THE STACK CLOSURE PRESSURE OF A BRAKE STACK

      
Application Number 16410730
Status Pending
Filing Date 2019-05-13
First Publication Date 2020-11-19
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 fluid pressure of the brake system, and one or more pressure transducers that generate a proportional electrical signal representative of the 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  ?

  • B64C 25/42 - Arrangement or adaptation of brakes
  • B64C 25/46 - Brake regulators for preventing skidding or aircraft somersaulting

63.

METHOD AND APPARATUS FOR DATA TRANSFER OVER A POWER LINE CONNECTION

      
Application Number 16411797
Status Pending
Filing Date 2019-05-14
First Publication Date 2020-11-19
Owner THE BOEING COMPANY (USA)
Inventor
  • Nguyen, Nha Thanh
  • Ya, Sopheap
  • Kumar, Anil

Abstract

A broadband over powerline (BPL) unit is provided. The BPL unit includes at least one processor programmed to execute a first virtual machine and a second virtual machine, at least one memory device in communication with the at least one processor, and a powerline transceiver. The at least one processor is programmed to transmit and receive data over a three-phase power line via the powerline transceiver. The at least one processor is also programmed to receive, via the first virtual machine, a first plurality of data for transmission via the powerline transceiver, receive, via the second virtual machine, a second plurality of data for transmission via the powerline transceiver, transmit, via the powerline transceiver, the first plurality of data via a first phase, and transmit, via the powerline transceiver, the second plurality of data via a second phase.

IPC Classes  ?

  • H04L 29/06 - Communication control; Communication processing characterised by a protocol
  • H04B 3/54 - Systems for transmission via power distribution lines
  • G06F 21/60 - Protecting data

64.

AIRCRAFT PANEL SYSTEM, AIRCRAFT, AND METHOD OF OPERATING THE AIRCRAFT PANEL SYSTEM

      
Application Number 16412603
Status Pending
Filing Date 2019-05-15
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Files, Joe
  • Logue, Adam A.

Abstract

An aircraft panel system including a first panel, having a hinged coupling configured to couple the first panel to an aircraft structure, a second panel disposed adjacent to the first panel such that the first panel and the second panel together form cabin surface of an aircraft, and a latch mechanism configured to releasably couple the second panel to the aircraft structure, where the first panel is configured to pivot about the hinged coupling from a latched position to an actuation position to actuate the latch mechanism and cause a release of the second panel from the latch mechanism.

IPC Classes  ?

  • E05B 63/22 - Locks with special structural characteristics operated by a pulling or pushing action perpendicular to the front plate
  • B64C 1/06 - Frames; Stringers; Longerons
  • E05F 1/10 - Closers or openers for wings, not otherwise provided for in this subclass spring-actuated for swinging wings
  • E05F 3/20 - Closers or openers with braking devices, e.g. checks; Construction of pneumatic or liquid braking devices in hinges
  • E05C 7/06 - Fastening devices specially adapted for two wings for wings which abut when closed a fastening device for one wing being actuated or controlled by closing another wing

65.

PARTICLE DISPERSION LAYER HAVING PERSISTENT MAGNETIC FIELD

      
Application Number 16413450
Status Pending
Filing Date 2019-05-15
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor Tillotson, Brian

Abstract

A spacecraft includes a body defining an interior payload region and a particle dispersion layer disposed between the interior payload region and one or more exterior surfaces of the body. The particle dispersion layer is formed of one or more magnets having a persistent magnetic field. The spacecraft including the particle dispersion layer may be manufactured by obtaining a particle dispersion layer having a persistent magnetic field, identifying a directionality of the persistent magnetic field of the particle dispersion layer, and installing the particle dispersion layer between an interior payload region formed by a body of a spacecraft and one or more exterior surfaces of the body according to the identified directionality of the persistent magnetic field.

IPC Classes  ?

66.

AIR DATA SYSTEM USING MAGNETICALLY INDUCED VOLTAGE

      
Application Number 16413465
Status Pending
Filing Date 2019-05-15
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor Tillotson, Brian

Abstract

An air data system for measuring an airspeed includes a pair of electrodes, and one or more magnets arranged relative to the pair of electrodes. The pair of electrodes includes a first electrode and a second electrode spaced apart from the first electrode along a first dimension by an air gap. The one or more magnets produce a magnetic field within the air gap. The air data system further includes an electronic circuit interfacing with the pair of electrodes. The electronic circuit outputs a voltage difference measured between the pair of electrodes across the air gap. A magnitude of the voltage difference indicates a magnitude of an air stream velocity through the air gap.

IPC Classes  ?

  • G01P 5/08 - Measuring speed of fluids, e.g. of air stream; Measuring speed of bodies relative to fluids, e.g. of ship, of aircraft by measuring variation of an electric variable directly affected by the flow, e.g. by using dynamo-electric effect
  • G01P 13/02 - Indicating direction only, e.g. by weather vane
  • G01F 1/58 - Measuring the volume flow or mass flow of fluid or fluent solid material wherein the fluid passes through the meter in a continuous flow by using electric or magnetic effects by electromagnetic flowmeters
  • G01F 1/60 - Circuits therefor

67.

Method of Testing Additive Manufactured Material and Additive Manufactured Parts

      
Application Number 16413752
Status Pending
Filing Date 2019-05-16
First Publication Date 2020-11-19
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 3/08 - Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces
  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma

68.

Fixture for Testing a Test Specimen

      
Application Number 16413855
Status Pending
Filing Date 2019-05-16
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Coad, Dennis Lynn
  • Senderos, Bruno Zamorano
  • King, Garnel
  • Meier, Stefanie Anita
  • Rodriguez, Rogie I.

Abstract

A test fixture configured to attach to and apply a tensile force to a test specimen. The test fixture may include a first clevis section and a second clevis section that are each configured to be attached to the test specimen. Each of the first and second clevis sections may include a fixed block and a movable block. Connectors connect the clevis sections together and hold the test specimen. The first and second clevis sections may be moved apart to apply a force to the attached test specimen to test one or more properties of the test specimen.

IPC Classes  ?

  • G01N 3/04 - Chucks
  • G01N 3/08 - Investigating strength properties of solid materials by application of mechanical stress by applying steady tensile or compressive forces

69.

STIFFENER ASSEMBLY APPLICATION SYSTEM WITH CARRIER FILM SET

      
Application Number 16415952
Status Pending
Filing Date 2019-05-17
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Knutson, Samuel James
  • Peters, Brian Timothy
  • Suriyaarachchi, Raviendra
  • Kendall, James R.
  • Shaw, Paul D.

Abstract

A carrier film set configured to apply a number of stiffener assemblies to a layup mandrel, the carrier film set comprising: a number of alignment features configured to align the carrier film set relative to the layup mandrel; and a number of indexing features configured to index the number of stiffener assemblies onto the carrier film set.

IPC Classes  ?

  • B29C 70/32 - 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 on a rotating mould, former or core
  • B64C 1/06 - Frames; Stringers; Longerons

70.

Method and System for Manufacturing Composite Structures Using a Magnesium Bladder

      
Application Number 16415985
Status Pending
Filing Date 2019-05-17
First Publication Date 2020-11-19
Owner The Boeing Company (USA)
Inventor
  • Shewchuk, Steven M.
  • Schell, Justin Joseph
  • Matlack, Michael Palmore
  • Verma, Ravi

Abstract

A composite manufacturing system and method are provided. The composite manufacturing system comprises a press and a bladder. The press has an upper portion having a desired shape for a composite structure and a lower portion configured to receive layers of composite material. The bladder is associated with the upper portion of the press and is configured to reach a superplastic state when heated such that the bladder forms to the composite structure by applying heat and pressure to the layers of composite material. The bladder cools without appreciable shrinkage, applying a desired amount of pressure to the composite structure during the entire cooling cycle. Once one composite structure is formed using the bladder, the bladder may be reused to form similar structures.

IPC Classes  ?

  • B29C 70/34 - 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 shaping or impregnating by compression

71.

Calibration procedure for establishing an extrinsic relationship between lidar and camera sensors

      
Application Number 16717953
Grant Number 10838049
Status In Force
Filing Date 2019-12-17
First Publication Date 2020-11-17
Grant Date 2020-11-17
Owner The Boeing Company (USA)
Inventor Schwiesow, Michael B.

Abstract

In one or more embodiments, a method for calibration between a lidar sensor and a camera comprises determining translation parameters of extrinsic calibration parameters by using a location of the camera with respect to the lidar sensor. The method further comprises orienting a target chessboard such that it is aligned with axes of a lidar coordinate system. Also, the method comprises optimizing a best fit transformation between a camera coordinate system and a target chessboard coordinate system. In addition, the method comprises determining a rotation matrix using the best fit transformation between the camera coordinate system and the target chessboard coordinate system. Additionally, the method comprises extracting Euler angles of the extrinsic calibration parameters from the rotation matrix. Also, the method comprises collecting, by the lidar sensor and the camera, calibration scenes using the target chessboard. Further, the method comprises optimizing the extrinsic calibration parameters by using the calibration scenes.

IPC Classes  ?

  • G01S 7/497 - Means for monitoring or calibrating
  • G01S 7/51 - Display arrangements
  • G06F 17/17 - Function evaluation by approximation methods, e.g. interpolation or extrapolation, smoothing or least mean square method
  • G06F 3/0484 - Interaction techniques based on graphical user interfaces [GUI] for the control of specific functions or operations, e.g. selecting or manipulating an object or an image, setting a parameter value or selecting a range
  • G06T 7/80 - Analysis of captured images to determine intrinsic or extrinsic camera parameters, i.e. camera calibration

72.

Systems and methods for navigating within a visual representation of a three-dimensional environment

      
Application Number 16588879
Grant Number 10839602
Status In Force
Filing Date 2019-09-30
First Publication Date 2020-11-17
Grant Date 2020-11-17
Owner The Boeing Company (USA)
Inventor Esposito, Christopher D.

Abstract

In an example, a method for navigating within a visual representation of a three-dimensional (3D) environment is described. The method includes detecting a selection of a translational input trigger at a translational origin in a translational input region of a user interface. The method includes detecting that the translational input trigger has been moved from the translational origin to a point on a translational control border. The method includes detecting that the translational input trigger has been moved from within the position direct control zone to a location within the position rate control zone. The method includes, responsive to detecting that the translational input trigger has been moved from within the position direct control zone to the location within the position rate control zone, translating the field of view in the visual representation of the 3D environment at a velocity corresponding to the location within the position rate control zone.

IPC Classes  ?

  • G06T 19/00 - Manipulating 3D models or images for computer graphics
  • G06T 15/20 - Perspective computation

73.

Method and system for independent-speed-variable-frequency-generator-based power system voltage regulation

      
Application Number 16590157
Grant Number 10840839
Status In Force
Filing Date 2019-10-01
First Publication Date 2020-11-17
Grant Date 2020-11-17
Owner THE BOEING COMPANY (USA)
Inventor
  • Gao, Lijun
  • Liu, Shengyi
  • Solodovnik, Eugene
  • Karimi, Kamiar

Abstract

A system may include an independent speed variable frequency (ISVF) generator and an excitation source configured to provide an excitation signal to rotor field windings of the ISVF generator to produce a rotating magnetic flux that is independent of a shaft speed of the ISVF generator. The system may include a bus configured to receive an output voltage of the ISVF generator. A generator control unit may be configured to generate a first excitation voltage reference component based on a shaft frequency of the ISVF generator, generate a second excitation voltage reference component based on a difference between a reference voltage and a measured output voltage of the ISVF generator, and generate an excitation voltage control signal based on a combination of the first excitation voltage reference component and the second excitation voltage reference component, the excitation voltage control signal usable to control a voltage magnitude of the excitation signal.

IPC Classes  ?

  • H02P 9/42 - Arrangements for controlling electric generators for the purpose of obtaining a desired output to obtain desired frequency without varying speed of the generator

74.

Cart apparatus with a top support having a plurality of openings

      
Application Number 29711338
Grant Number D0902520
Status In Force
Filing Date 2019-10-30
First Publication Date 2020-11-17
Grant Date 2020-11-17
Owner The Boeing Company (USA)
Inventor Childress, Jamie J.

75.

COMPOSITIONALLY MODULATED ZINC-IRON MULTILAYERED COATINGS

      
Application Number 16940934
Status Pending
Filing Date 2020-07-28
First Publication Date 2020-11-12
Owner THE BOEING COMPANY (USA)
Inventor
  • Gaydos, Stephen P.
  • Ijeri, Vijaykumar S.
  • Prakash, Om
  • Mishra, Trilochan
  • Singh, Raghuvir
  • Tiwari, Shashi Kant

Abstract

The present disclosure provides electrolyte solutions for electrodeposition of zinc-iron alloys, methods of forming electrolyte solutions, and methods of electrodepositing zinc-iron alloys. An electrolyte solution for electroplating can include an alkali metal citrate, an alkali metal acetate, a citric acid, and glycine with a metal salt. An electrolyte solution can be formed by dissolving an alkali metal citrate, an alkali metal acetate, a citric acid, and glycine in water or an aqueous solution. Electrodepositing zinc-iron alloys on a substrate can include introducing a cathode and an anode into an electrolyte solution comprising an alkali metal citrate, an alkali metal acetate, a citric acid, and glycine. Electrodepositing can further include passing a current between the cathode and the anode through the electrolyte solution to deposit zinc and iron onto the cathode.

IPC Classes  ?

  • C25D 3/24 - Electroplating; Baths therefor from solutions of zinc from cyanide baths
  • C25D 5/12 - Electroplating with more than one layer of the same or of different metals at least one layer being of nickel or chromium
  • C25D 3/56 - Electroplating; Baths therefor from solutions of alloys
  • C25D 3/54 - Electroplating; Baths therefor from solutions of metals not provided for in groups
  • C25D 5/18 - Electroplating using modulated, pulsed or reversing current
  • B22F 3/105 - Sintering only by using electric current, laser radiation or plasma
  • C25D 5/10 - Electroplating with more than one layer of the same or of different metals

76.

Single-Piece Extended Laminar Flow Inlet Lipskin

      
Application Number 16942907
Status Pending
Filing Date 2020-07-30
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Leon, Luis R.
  • Saha, Pradip K.
  • Oliver, Carol S.
  • Johnson, Ricole A.

Abstract

Methods are disclosed for forming metal workpieces made from a heat-treatable metal that has been shaped and tempered according to specified protocols that facilitate formation of large contoured unitary metal structures having welds that are retained in the finished structure, and finished metal structures made according to such methods.

IPC Classes  ?

  • B23K 20/00 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
  • B64D 33/02 - Arrangement in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
  • B23K 20/12 - Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating the heat being generated by friction; Friction welding

77.

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

      
Application Number 16404297
Status Pending
Filing Date 2019-05-06
First Publication Date 2020-11-12
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  ?

  • G01N 15/02 - Investigating particle size or size distribution

78.

FOLDING MAIN LANDING GEAR FOR CARGO AIRCRAFT

      
Application Number 16405789
Status Pending
Filing Date 2019-05-07
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor Cottet, Justin Duane

Abstract

Systems and methods for folding landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a yoke pivotally coupled with the shock strut via a lower trunnion, and pivotally coupled with an aircraft structure via an upper trunnion. The yoke is configured to pivot about the upper trunnion in a direction back toward a tail of the aircraft and up toward a fuselage of the aircraft, and the shock strut is configured to pivot about the lower trunnion in a direction forward toward a nose of the aircraft and up toward the fuselage of the aircraft to retract the one or more wheels.

IPC Classes  ?

  • B64C 25/14 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like fore-and-aft
  • B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
  • B64C 25/16 - Fairings movable in conjunction with undercarriage elements
  • B64C 25/18 - Operating mechanisms

79.

LANDING GEAR FOR CARGO AIRCRAFT

      
Application Number 16405794
Status Pending
Filing Date 2019-05-07
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Schmidt, Gregory M.
  • Cottet, Justin Duane

Abstract

Systems and methods for wide set retracting landing gear of a cargo aircraft. One embodiment is an aircraft that includes a fuselage including a nose, and a pair of main landing gears comprising a pair of main posts disposed across the fuselage, each main post having a main wheel and configured to pivot forward toward the nose to retract the main wheel. The aircraft also includes a pair of nose landing gears comprising a pair of nose posts disposed across the fuselage, each nose post having a nose wheel and configured to pivot inboard to retract the nose wheel.

IPC Classes  ?

  • B64C 25/12 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
  • B64C 25/18 - Operating mechanisms
  • B64C 25/16 - Fairings movable in conjunction with undercarriage elements
  • B64C 25/14 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like fore-and-aft
  • B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies

80.

Zero-G Lift Assist Device

      
Application Number 16406126
Status Pending
Filing Date 2019-05-08
First Publication Date 2020-11-12
Owner
  • The Boeing Company (USA)
  • University of Washington (USA)
Inventor
  • Shehab, Kareem
  • Coffland, Donald W.
  • De Marne, Alexander
  • Piaskowy, W. Tony
  • Fasola, Cameron
  • Mccann, Lance O.

Abstract

Apparatuses, systems, and methods are disclosed for providing a zero-G condition to a part to assist in allowing an operator to weightlessly move a part and assist an operator in the installation of a part into an assembly. Present methods, systems, and apparatuses further provide a zero-G lift able to alter the lift velocity of a part, from first predetermined velocity to a second predetermined velocity.

IPC Classes  ?

  • F16M 11/18 - Heads with mechanism for moving the apparatus relatively to the stand
  • F16M 11/04 - Means for attachment of apparatus; Means allowing adjustment of the apparatus relatively to the stand
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor
  • B66F 3/10 - Devices, e.g. jacks, adapted for uninterrupted lifting of loads screw-operated with telescopic sleeves
  • G01L 5/00 - Apparatus for, or methods of, measuring force, work, mechanical power, or torque, specially adapted for specific purposes
  • G01G 19/08 - Weighing apparatus or methods adapted for special purposes not provided for in groups for incorporation in vehicles
  • G05D 15/01 - Control of mechanical force or stress; Control of mechanical pressure characterised by the use of electric means
  • G05D 13/62 - Control of linear speed; Control of angular speed; Control of acceleration or deceleration, e.g. of a prime mover characterised by the use of electric means, e.g. use of a tachometric dynamo, use of a transducer converting an electric value into a displacement

81.

NAVIGATION PERFORMANCE IN URBAN AIR VEHICLES

      
Application Number 16406514
Status Pending
Filing Date 2019-05-08
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Kim, Geun Il
  • Feng, Gang

Abstract

A method performed by an air vehicle having navigational equipment includes receiving an actual navigation performance (ANP) value from a neighboring air vehicle. The method also includes displaying a representation of the air vehicle and a representation of the neighboring air vehicle on a display. The method also includes determining a combined ANP (CANP) value based on the ANP value from the neighboring air vehicle and an ANP value of the air vehicle. The method also includes comparing a position of the air vehicle to the CANP value. The method also includes responsive to the position of the air vehicle being within a distance margin away from the neighboring air vehicle based on the CANP value, performing an action to increase a distance the air vehicle is from the neighboring vehicle.

IPC Classes  ?

  • G08G 5/04 - Anti-collision systems
  • G08G 5/00 - Traffic control systems for aircraft
  • G05D 1/10 - Simultaneous control of position or course in three dimensions
  • G06F 17/11 - Complex mathematical operations for solving equations

82.

VORTEX REDUCTION APPARATUS FOR USE WITH AIRFOILS

      
Application Number 16406867
Status Pending
Filing Date 2019-05-08
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor Walliser, Eric W.

Abstract

Vortex reduction apparatus for use with airfoils are disclosed. An example vortex reduction apparatus includes a housing to couple to a tip of an airfoil. The housing defines a volute fluid flow passageway between an inlet and an outlet. The volute fluid flow passageway is structured to induce a rotational fluid flow in a first rotational direction opposite a second rotational direction of a shed vortex induced at the tip of the airfoil during flight.

IPC Classes  ?

  • B64C 23/06 - Influencing air-flow over aircraft surfaces, not otherwise provided for by generating vortices
  • B64C 3/58 - Wings provided with fences or spoilers
  • B64C 27/82 - Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting-rotor torque or changing direction of rotorcraft

83.

METHOD AND APPARATUS FOR ADVANCED SECURITY SYSTEMS OVER A POWER LINE CONNECTION

      
Application Number 16406958
Status Pending
Filing Date 2019-05-08
First Publication Date 2020-11-12
Owner THE BOEING COMPANY (USA)
Inventor
  • Ya, Sopheap
  • Nguyen, Nha Thanh

Abstract

A multifactor authentication system onboard a vehicle including at least one processor, a first database, a second database, and one or more protected computer systems is provided. The at least one processor is programmed to receive, from a user, a request for access to the one or more protected computer systems, wherein the request contains authentication information including a first authentication factor and a second authentication factor, retrieve first factor authentication data associated with the user from the first database, compare the first factor authentication data with the received first authentication factor to determine if there is a match, retrieve the second factor authentication data associated with the user from the second database, compare the second factor authentication data with the received second authentication factor to determine if there is a match, and grant access to the one or more protected computer systems if all of the comparisons match.

IPC Classes  ?

  • H04L 29/06 - Communication control; Communication processing characterised by a protocol
  • G06F 21/60 - Protecting data
  • H04L 9/32 - Arrangements for secret or secure communication including means for verifying the identity or authority of a user of the system
  • H04W 12/06 - Authentication
  • H04B 3/54 - Systems for transmission via power distribution lines

84.

TRANSPORT-BASED SYNTHETIC APERTURE RADAR NAVIGATION SYSTEMS AND METHODS

      
Application Number 16407460
Status Pending
Filing Date 2019-05-09
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Rao, Shankar R.
  • Ni, Kang-Yu
  • Kolouri, Soheil

Abstract

Systems and methods according to one or more embodiments are provided for registration of synthetic aperture range profile data to aid in SAR-based navigation. In one example, a SAR-based navigation system includes a memory comprising a plurality of executable instructions. The SAR-based navigation system further includes a processor adapted to receive range profile data associated with observed views of a scene, compare the range profile data to a template range profile data of the scene, and estimate registration parameters associated with the range profile data relative to the template range profile data to determine a deviation from the template range profile data.

IPC Classes  ?

  • G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques

85.

CARGO AERIAL DELIVERY SYSTEMS AND RELATED METHODS

      
Application Number 16407812
Status Pending
Filing Date 2019-05-09
First Publication Date 2020-11-12
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  ?

  • B64C 39/02 - Aircraft not otherwise provided for characterised by special use
  • G05D 1/10 - Simultaneous control of position or course in three dimensions
  • B64D 1/22 - Taking-up articles from earth's surface
  • B64D 1/12 - Releasing
  • G06Q 10/08 - Logistics, e.g. warehousing, loading, distribution or shipping; Inventory or stock management, e.g. order filling, procurement or balancing against orders

86.

CARGO CONTAINERS

      
Application Number 16408152
Status Pending
Filing Date 2019-05-09
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor Polus, Jeffrey Edward

Abstract

Cargo containers are disclosed herein. A cargo container for carrying one or more delivery items to respective delivery destinations may include a container body configured to at least partially enclose and support the delivery item(s) and to be selectively and operatively coupled to a vehicle. The cargo container additionally may include a programmable device supported by the container body that stores manifest information regarding each delivery item. The cargo container further may include a container communication device supported by the container body and configured to convey delivery information to a vehicle communication device of the vehicle to direct the vehicle to the delivery destination(s) of the delivery item(s). The manifest information may include item destination information that represents the delivery destination of each delivery item, and the delivery information may be at least partially based upon the item destination information.

IPC Classes  ?

  • B65D 25/22 - External fittings for facilitating lifting or suspending of containers
  • G06Q 10/08 - Logistics, e.g. warehousing, loading, distribution or shipping; Inventory or stock management, e.g. order filling, procurement or balancing against orders
  • B64D 9/00 - Equipment for handling freight; Equipment for facilitating passenger embarkation or the like
  • B63B 25/00 - Load-accommodating arrangements, e.g. stowing or trimming; Vessels characterised thereby
  • G06Q 50/28 - Logistics, e.g. warehousing, loading, distribution or shipping
  • B64D 1/08 - Dropping, ejecting, or releasing articles the articles being load-carrying devices
  • B64D 1/22 - Taking-up articles from earth's surface

87.

Composite Stringer and Methods for Forming a Composite Stringer

      
Application Number 16408398
Status Pending
Filing Date 2019-05-09
First Publication Date 2020-11-12
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
  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
  • B32B 1/00 - Layered products essentially having a general shape other than plane
  • B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers

88.

Composite Stringer and Methods for Forming a Composite Stringer

      
Application Number 16408406
Status Pending
Filing Date 2019-05-09
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor Cheng, Jiangtian

Abstract

In an example, a composite stringer assembly includes a composite stringer, a radius filler, and an overwrap layer. The composite stringer includes: (i) a skin flange configured to be coupled to a support structure, (ii) a web, (iii) a lower corner portion of the composite stringer extending from the skin flange to the web, and (iv) an inner surface of the composite stringer extending along the skin flange, the lower corner portion, and the web. The radius filler includes a first surface coupled to the inner surface at the lower corner portion, a second surface configured to couple to the support structure, and a third surface extending between the first surface and the second surface. The overwrap layer is coupled to the inner surface at the web, the third surface of the radius filler, and the support structure.

IPC Classes  ?

  • B64C 1/06 - Frames; Stringers; Longerons
  • B64C 1/00 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like
  • B64C 1/12 - Construction or attachment of skin panels
  • B32B 1/00 - Layered products essentially having a general shape other than plane
  • B32B 5/12 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by structural features of a layer comprising fibres or filaments characterised by the relative arrangement of fibres or filaments of adjacent layers

89.

Composite Structure Having a Variable Gage and Methods for Forming a Composite Structure Having a Variable Gage

      
Application Number 16408408
Status Pending
Filing Date 2019-05-09
First Publication Date 2020-11-12
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  ?

  • B29C 70/06 - Fibrous reinforcements only
  • 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 5/14 - Layered products characterised by the non-homogeneity or physical structure of a layer characterised by a layer differing constitutionally or physically in different parts, e.g. denser near its faces
  • 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
  • B32B 3/10 - 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 discontinuous layer, i.e. apertured or formed of separate pieces of material

90.

TITANIUM-BASED ALLOY AND METHOD FOR MANUFACTURING A TITANIUM-BASED ALLOY COMPONENT BY AN ADDITIVE MANUFACTURING PROCESS

      
Application Number 16832072
Status Pending
Filing Date 2020-03-27
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Cotton, James D.
  • Ghabchi, Arash
  • Crill, Matthew J.
  • Mitropolskaya, Natalia G.

Abstract

An alpha-beta titanium-based alloy including titanium; one of 0.001-1.0 wt. % neodymium, 0.001-1.0 wt. % dysprosium, or 0.001-0.5 wt. % erbium; and at least one of aluminum, zirconium, tin, oxygen, molybdenum, vanadium, niobium, iron, and chromium present in amounts defined based on an aluminum equivalent and a molybdenum equivalent, wherein the aluminum equivalent (Al-eq) is between 0 to 7.5% and the molybdenum equivalent (Mo-eq) is between 2.7 to 47.5, and wherein the aluminum equivalent (Al-eq) and the molybdenum equivalent (Mo-eq) are defined, in weight percents, as follows: An alpha-beta titanium-based alloy including titanium; one of 0.001-1.0 wt. % neodymium, 0.001-1.0 wt. % dysprosium, or 0.001-0.5 wt. % erbium; and at least one of aluminum, zirconium, tin, oxygen, molybdenum, vanadium, niobium, iron, and chromium present in amounts defined based on an aluminum equivalent and a molybdenum equivalent, wherein the aluminum equivalent (Al-eq) is between 0 to 7.5% and the molybdenum equivalent (Mo-eq) is between 2.7 to 47.5, and wherein the aluminum equivalent (Al-eq) and the molybdenum equivalent (Mo-eq) are defined, in weight percents, as follows: Al-eq=(Al %)+(Zr %)/6+(Sn %)/3+10*(O %) An alpha-beta titanium-based alloy including titanium; one of 0.001-1.0 wt. % neodymium, 0.001-1.0 wt. % dysprosium, or 0.001-0.5 wt. % erbium; and at least one of aluminum, zirconium, tin, oxygen, molybdenum, vanadium, niobium, iron, and chromium present in amounts defined based on an aluminum equivalent and a molybdenum equivalent, wherein the aluminum equivalent (Al-eq) is between 0 to 7.5% and the molybdenum equivalent (Mo-eq) is between 2.7 to 47.5, and wherein the aluminum equivalent (Al-eq) and the molybdenum equivalent (Mo-eq) are defined, in weight percents, as follows: Al-eq=(Al %)+(Zr %)/6+(Sn %)/3+10*(O %) Mo-eq=(Mo %)+0.67*(V %)+0.33*(Nb %)+2.9*(Fe %)+1.6*(Cr %).

IPC Classes  ?

  • C22C 14/00 - Alloys based on titanium
  • B33Y 10/00 - Processes of additive manufacturing
  • B33Y 70/00 - Materials specially adapted for additive manufacturing

91.

PREDICTIVE PART MAINTENANCE

      
Application Number 16866369
Status Pending
Filing Date 2020-05-04
First Publication Date 2020-11-12
Owner THE BOEING COMPANY (USA)
Inventor
  • Wang, Zhennong
  • Arita, Michael M.

Abstract

The present disclosure provides for predictive part maintenance by identifying component service programs indicating one or more components to track usage of in one or more aircraft for a given time period; tracking component usage in the one or more aircraft for the one or more components to identify scheduled removals for instances of the one or more components within the given time period; amalgamating component removals across the one or more aircraft for the one or more components; amalgamating component demand across the component service programs for the one or more components based on the scheduled removals and the component removals; and generating and transmitting an inventory alert based on the component demand.

IPC Classes  ?

  • 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
  • B64D 45/00 - Aircraft indicators or protectors not otherwise provided for

92.

CONFORMAL LOAD BEARING DISTRIBUTED SENSING ARRAYS

      
Application Number 16936903
Status Pending
Filing Date 2020-07-23
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Urcia, Manny S.
  • St. Clair, Jonathan M.
  • La Fata, Christopher M.
  • Castagno, John G.
  • Butterfield, Ordie D.
  • Tyahla, Stephen T.
  • Adams, Alec
  • Cai, Lixin

Abstract

Systems, methods, and apparatus for an electromagnetic (EM) panel are disclosed. In one or more embodiments, a disclosed electromagnetic (EM) panel comprises an outer skin, an inner skin, a core disposed between the outer skin and the inner skin, and at least one receiver to receive at least one first signal. In at least one embodiment, at least one receiver is disposed within an opening on the outer skin of the EM panel. At least one receiver is an optical sensor(s) and/or a radio frequency (RF) antenna(s). In one or more embodiments, the EM panel further comprises at least one transmitter to transmit at least one second signal. In at least one embodiment, at least one transmitter is disposed within an opening on the outer skin of the EM panel. At least one transmitter is a laser(s) and/or a RF antenna(s).

IPC Classes  ?

  • H04B 10/112 - Line-of-sight transmission over an extended range
  • H04B 10/50 - Transmitters
  • H04B 10/66 - Non-coherent receivers, e.g. using direct detection
  • 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
  • H01Q 5/22 - RF wavebands combined with non-RF wavebands, e.g. infrared or optical
  • G01S 17/42 - Simultaneous measurement of distance and other coordinates
  • H04B 7/185 - Space-based or airborne stations
  • G01S 13/90 - Radar or analogous systems, specially adapted for specific applications for mapping or imaging using synthetic aperture techniques
  • G01S 13/42 - Simultaneous measurement of distance and other coordinates

93.

SYSTEMS AND METHODS OF MONITORING A THERMAL PROTECTION SYSTEM

      
Application Number 16941239
Status Pending
Filing Date 2020-07-28
First Publication Date 2020-11-12
Owner THE BOEING COMPANY (USA)
Inventor
  • Georgeson, Gary
  • Safai, Morteza

Abstract

A method of monitoring a thermal protection system coupled to a structural component is provided. The thermal protection system includes a thermally insulative body and at least one layer of thermochromatic material applied thereon such that the at least one layer is positioned between the thermally insulative body and the structural component. The method includes determining a value of a thermochromatic property of the at least one layer of thermochromatic material, wherein the value of the thermochromatic property is responsive to an amount of heat applied to the at least one layer of thermochromatic material, comparing the value to a baseline value of the thermochromatic property, and determining degradation of the thermal protection system when the value of the thermochromatic property deviates from the baseline value.

IPC Classes  ?

  • G01N 25/72 - Investigating presence of flaws
  • G01K 11/12 - Measuring temperature based on physical or chemical changes not covered by group , , , or using change of colour or translucency

94.

FRICTION FIT ELECTROMAGNETIC EFFECT PROTECTION CAP SYSTEM

      
Application Number 16403842
Status Pending
Filing Date 2019-05-06
First Publication Date 2020-11-12
Owner THE BOEING COMPANY (USA)
Inventor
  • Stevens, Bart
  • Cowan, Daniel J.
  • Auffinger, Sean

Abstract

A protective seal cap assembly for enclosing an end portion of a fastener extending through a structure, which includes a cap member. The cap member includes a sidewall which defines an opening and defines an interior space within the sidewall and aligned with the opening, wherein the sidewall defines a central axis. The cap member further includes at least one rib which extends away from an interior surface of the sidewall within the interior space and extends in a direction along the central axis of the cap member.

IPC Classes  ?

95.

Systems and Methods for Transferring Mechanical Power in a Turbine Engine

      
Application Number 16404045
Status Pending
Filing Date 2019-05-06
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Foutch, David W.
  • Dirusso, Joseph M.
  • Karnofski, Kent E.

Abstract

A system (166) for transferring mechanical power in a turbine engine (150/151) including a low pressure spool (162) and a high pressure spool (156) includes a power transfer unit (168) coupled between an output shaft (172) of the low pressure spool (162) and a drive shaft (174) of the high pressure spool (156) to mechanically link the low pressure spool (162) to the high pressure spool (156), and a clutch (170) coupled to the power transfer unit (168), wherein the clutch (170) is configured to transfer power produced from the low pressure spool (162) to the high pressure spool (156).

IPC Classes  ?

  • F02C 7/36 - Power transmission between the different shafts of the gas-turbine plant, or between the gas-turbine plant and the power user
  • F02C 7/32 - Arrangement, mounting, or driving, of auxiliaries
  • F02C 9/18 - Control of working fluid flow by bleeding, by-passing or acting on variable working fluid interconnections between turbines or compressors or their stages
  • F02C 3/107 - Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
  • F01D 19/00 - Starting of machines or engines; Regulating, controlling, or safety means in connection therewith
  • F02C 7/26 - Starting; Ignition
  • F02K 3/06 - Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low-pressure outputs, for augmenting jet thrust, e.g. of double-flow type with front fan
  • F16D 41/069 - Freewheels or freewheel clutches with intermediate wedging coupling members between an inner and an outer surface the intermediate members wedging by pivoting or rocking, e.g. sprags
  • B64D 31/06 - Initiating means actuated automatically
  • B64D 31/14 - Transmitting means between initiating means and power plants
  • B64D 35/02 - Transmitting power from power plant to propellers or rotors; Arrangements of transmissions characterised by the type of power plant
  • F01D 25/34 - Turning or inching gear

96.

METHOD AND APPARATUS FOR AUXILIARY POWER UNIT INSTALLATION

      
Application Number 16404559
Status Pending
Filing Date 2019-05-06
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Wong, Alan J.
  • Call, Curtis John
  • Arnold, Theodore Carl

Abstract

An aircraft is disclosed, including a fuselage having a compartment configured to house refueling apparatus. An auxiliary power unit is mounted in the compartment.

IPC Classes  ?

  • B64D 41/00 - Power installations for auxiliary purposes
  • B64D 27/26 - Aircraft characterised by construction of power-plant mounting
  • B64C 1/16 - Fuselages; Constructional features common to fuselages, wings, stabilising surfaces, or the like specially adapted for mounting power plant

97.

SEAT TRACK FITTINGS AND METHODS FOR INSTALLING PASSENGER SEATS IN AIRCRAFT CABINS USING SEAT TRACK FITTINGS

      
Application Number 16404977
Status Pending
Filing Date 2019-05-07
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor
  • Grewal, Gagandeep Inder Singh
  • Kim, Jason B.
  • Natale, Angela

Abstract

Provided are seat track fittings and methods for installing passenger seats in aircraft cabins using these seat track fittings such that the same seat can be installed on different types of seat tracks. A seat track fitting comprises a leg support, a pin, and a base interconnecting the leg support and pin. During installation of the seat track fitting, the pin is inserted into an attachment opening of the seat track. The attachment opening is selected based on the desired position of a seat. A removable fastener then protrudes through the base of the seat track fitting and is inserted into another attachment opening of the seat track. The seat is then attached to the seat track fitting by inserting the stud end of the seat into the leg support of the seat track fitting and fixing the stud end within the leg support.

IPC Classes  ?

  • B64D 11/06 - Arrangements or adaptations of seats
  • B64F 5/10 - Manufacturing or assembling aircraft, e.g. jigs therefor

98.

Selectable volume precision liquid dispenser

      
Application Number 16405253
Grant Number 10836539
Status In Force
Filing Date 2019-05-07
First Publication Date 2020-11-12
Grant Date 2020-11-17
Owner THE BOEING COMPANY (USA)
Inventor
  • Cousins, Clifford G.
  • Patel, Mitesh

Abstract

A selectable volume precision liquid dispenser apparatus and method of use. The dispenser apparatus includes a graduated, segmented elastic body with an interior space having different regions corresponding to different volumes where different liquid containing chambers are separated by one-way valves. Pressure applied by a user to one of the different chambers causes the dispensing of a precise amount of liquid through an inner conducting tube having openings to receive liquid in each of the different regions, and an outlet for dispensed the liquid. Release of the pressure allows the elastic body to return towards its original (resting) shape and draw liquid from a reservoir into the previously dispensed region in preparation for the next dispensing operation.

IPC Classes  ?

  • B65D 35/02 - Body construction
  • B65D 35/40 - Pliable tubular containers adapted to be permanently deformed to expel contents, e.g. collapsible tubes for toothpaste or other plastic or semi-liquid material; Holders therefor with auxiliary devices for metering discharge
  • B65D 35/22 - Pliable tubular containers adapted to be permanently deformed to expel contents, e.g. collapsible tubes for toothpaste or other plastic or semi-liquid material; Holders therefor with two or more compartments
  • B65D 35/28 - Pliable tubular containers adapted to be permanently deformed to expel contents, e.g. collapsible tubes for toothpaste or other plastic or semi-liquid material; Holders therefor with auxiliary devices for expelling contents
  • B65D 35/44 - Closures
  • G01F 11/08 - Apparatus requiring external operation adapted at each repeated and identical operation to measure and separate a predetermined volume of fluid or fluent solid material from a supply or container, without regard to weight, and to deliver it with measuring chambers which expand or contract during measurement of the diaphragm or bellows type
  • G01F 11/12 - Apparatus requiring external operation adapted at each repeated and identical operation to measure and separate a predetermined volume of fluid or fluent solid material from a supply or container, without regard to weight, and to deliver it with measuring chambers moved during operation of the valve type, i.e. the separating being effected by fluid-tight or powder-tight movements

99.

PIVOTING MAIN LANDING GEAR FOR CARGO AIRCRAFT

      
Application Number 16405763
Status Pending
Filing Date 2019-05-07
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor Cottet, Justin Duane

Abstract

Systems and methods for pivoting main landing gear of a cargo aircraft. One embodiment is a main landing gear of an aircraft that includes a shock strut coupled to a truck with one or more wheels, and a trunnion coupled to a bulkhead and configured to pivotally couple the shock strut with the bulkhead. The main landing gear also includes a folding brace extending from the shock strut in a forward direction toward a nose of the aircraft and configured to stabilize the shock strut. The main landing gear further includes a retraction actuator configured to pivot the shock strut about the trunnion to retract the one or more wheels in the forward direction toward the nose and up toward a fuselage of the aircraft.

IPC Classes  ?

100.

BIPEDAL NOSE LANDING GEAR FOR CARGO AIRCRAFT

      
Application Number 16405781
Status Pending
Filing Date 2019-05-07
First Publication Date 2020-11-12
Owner The Boeing Company (USA)
Inventor Cottet, Justin Duane

Abstract

Systems and methods for bipedal nose landing gear of an aircraft. One embodiment is a nose landing gear of an aircraft. The nose landing gear includes a shock strut coupled to an axle with a nose wheel, and a folding side brace extending from the shock strut inboard toward a belly of the aircraft and configured to stabilize the shock strut. The nose landing gear also includes a trunnion configured to pivot the shock strut forward toward a nose and inboard toward the belly of the aircraft to retract the nose wheel.

IPC Classes  ?

  • B64C 25/12 - Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
  • B64C 25/34 - Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
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