The Boeing Company patent applications on February 20th, 2025
Patent Applications by The Boeing Company on February 20th, 2025
The Boeing Company: 21 patent applications
The Boeing Company has applied for patents in the areas of H01M8/04007 (4), B64D27/355 (3), B64D37/30 (3), B64D13/08 (3), F17C9/00 (2) B64D13/08 (2), B21D5/004 (1), B64C3/36 (1), G06V20/13 (1), G06T7/20 (1)
With keywords such as: heat, configured, nacelle, surface, material, air, through, liquid, aircraft, and conduit in patent application abstracts.
Patent Applications by The Boeing Company
Inventor(s): Michael C. Elford of Brisbane (AU) for the boeing company
IPC Code(s): B21D5/00, B21D31/00
CPC Code(s): B21D5/004
Abstract: a computer-implemented method of generating an addendum surface for use in forming a sheet metal part by using an incremental sheet forming (isf) manufacturing process, wherein the method includes: providing a computer aided design (cad) geometry of the sheet metal part to be formed; and generating an addendum surface that surrounds and extends the cad geometry; wherein the addendum surface has a constant slope everywhere and has no regions of self-intersection. the addendum surface can be used to manufacture a male and/or a female underform tool for use in the isf process, such as two-point incremental forming (tpif). the addendum surface has a user-specified constant design wall angle, �, which can be selected to prevent tearing of sheet metal parts during isf due to excessive thinning at large wall angles (i.e., wall angles greater than 60�).
Inventor(s): James M. Giffin of San Antonio TX (US) for the boeing company
IPC Code(s): B23B49/02
CPC Code(s): B23B49/023
Abstract: a jig for forming holes in a workpiece includes a body. the body includes a first jig-surface and a second jig-surface. the first jig-surface includes a jig-surface contour. the jig-surface contour is complementary to a workpiece-surface contour of a workpiece-surface of the workpiece. the second jig-surface is planar and opposite to the first jig-surface. the jig includes through holes that extend through the body between the first jig-surface and the second jig-surface for forming holes in the workpiece. each one of the through holes includes a through-hole axis that is perpendicular to the second jig-surface and that is non-perpendicular to the first jig-surface such that each one of the holes formed in the workpiece has a hole axis that is non-perpendicular to the workpiece-surface.
Inventor(s): Daniel R. Smith of Woodinville WA (US) for the boeing company, Darrell D. Jones of Mill Creek WA (US) for the boeing company, Monte D. Wright of Kenmore WA (US) for the boeing company
IPC Code(s): B26D7/32, B64C1/06, B64C1/14, B64F5/10
CPC Code(s): B26D7/32
Abstract: apparatus and methods are provided for fabrication of a structure, for example, a half barrel section of a fuselage. the apparatus includes an indexing unit dimensioned for coupling to an indexing feature disposed on the structure. the structure proceeds along a process direction during fabrication. a cutting station cuts out manufacturing excess from the structure to form, for example, openings for windows and doors. a method for fabrication of a structure includes indexing a structure to a cutting station based on an indexing feature associated or located on the structure. the method includes operating the cutting station to cut manufacturing excess from the structure. a method includes removing cut sections of the manufacturing excess and routing these sections away from the cutting station.
Inventor(s): Michael Harris Larson of Mercer Island WA (US) for the boeing company, Marcus Anthony Belcher of Sammamish WA (US) for the boeing company, Gwendolyn Marie Janda of Seattle WA (US) for the boeing company, Gregory Martin Reyneke of Seattle WA (US) for the boeing company, Ying Shi of St. Louis MO (US) for the boeing company
IPC Code(s): B32B7/023, B32B27/08, B32B27/28, B32B37/18
CPC Code(s): B32B7/023
Abstract: thermoplastic composite material structures comprise a multi-region thermoplastic surfacing film layer that further comprises first and second regions within the multi-region thermoplastic surfacing film layer having visually-detectable colors different from one another to facilitate surfacing film layer processing, and processing of the thermoplastic composite material stack.
20250058557. Multi-Ply Lamination System_simplified_abstract_(the boeing company)
Inventor(s): Shuonan Dong of Seattle WA (US) for the boeing company, Austin B. Ball of Mercer Island WA (US) for the boeing company, Alan Scott Locke of Federal Way WA (US) for the boeing company, Asher Seth Einhorn of Seattle WA (US) for the boeing company, Brice Aaron Johnson of Toledo WA (US) for the boeing company
IPC Code(s): B32B38/18, B32B5/12, B32B37/18, B32B38/00, B32B41/00
CPC Code(s): B32B38/185
Abstract: a method forms a multi-ply laminate. a first cutting system cuts and moves a first group of courses into staging positions. placement robots pick up and place the first group of courses from the staging positions to a layup surface to form a first ply of the multi-ply laminate, changing an orientation of fibers from an initial orientation to a desired orientation for the first ply. a second cutting system cuts and moves a second group of courses into the staging positions while the placement robots are picking up and placing the first group of courses. the placement robots pick up and place the second group of courses from the staging positions to the layup surface to form a second ply of the multi-ply laminate after the first ply has been formed, changing the orientation of the fibers from the initial orientation to the desired orientation for the second ply.
20250058866. Thresholds for Flooring in an Aircraft_simplified_abstract_(the boeing company)
Inventor(s): Rick Eugene SHEPHERD of Arlington WA (US) for the boeing company
IPC Code(s): B64C1/18, B32B3/08, B32B5/02, B32B27/08, B32B27/30, B32B27/40, B32B37/12
CPC Code(s): B64C1/18
Abstract: thresholds for flooring in an aircraft are described herein. an example aircraft includes a subfloor, first flooring material on the subfloor, second flooring material on the subfloor, and a threshold at least partially between the first flooring material and the second flooring material. the threshold includes a vertical body portion having a top surface, a bottom surface, a first side surface, and a second side surface. the vertical body portion has a concave area extending into the second side surface at the bottom surface, and wherein a second edge of the second flooring material extends into the concave area. the threshold also includes a ramp portion extending from the first side surface. the ramp portion has a decreasing thickness from the vertical body portion to a distal end of the ramp portion. the ramp portion is positioned between a portion of the first flooring material and the subfloor.
20250058867. Insulation Blanket Assemblies and Methods_simplified_abstract_(the boeing company)
Inventor(s): Steven Scott of Newcastle WA (US) for the boeing company, Valeriy Vinogradov of Kent WA (US) for the boeing company, Alan Lagervall of Pacific WA (US) for the boeing company, Mehmet Volkan of Renton WA (US) for the boeing company, Sara Walter of Federal Way WA (US) for the boeing company
IPC Code(s): B64C1/40
CPC Code(s): B64C1/403
Abstract: an insulation blanket assembly for use on an aircraft includes a cover. the cover has an inboard material and an outboard material. the insulation blanket assembly also includes an insulation material between the inboard material and the outboard material. the insulation blanket assembly also includes one or more support rails attached to at least one of the cover or the insulation material. when the insulation blanket assembly is attached to the aircraft, the one or more support rails are configured to provide separation between an aircraft structure and the insulation material to reduce or eliminate moisture from transferring to the insulation material.
Inventor(s): Chellappa Balan of Mason OH (US) for the boeing company, Charles Aguilar of Arlington VA (US) for the boeing company
IPC Code(s): B64D13/08, B60L50/72, B60L58/33, B64D13/00, H01M8/04007, H01M8/04029
CPC Code(s): B64D13/08
Abstract: aircraft comprises a heater system, a conduit system thermally connected to fuel cell stacks, a pump system, and a controller. the heater system is configured to heat a coolant. the coolant flows through the conduit system. the pump system is configured to circulate the coolant through the conduit system to the fuel cell stacks. the controller is configured to control the heater system to heat the coolant to form a heated coolant. the controller is configured to control the pump system to circulate the heated coolant through the conduit system. the controller is configured to control the conduit system to circulate the heated coolant to a subset of the fuel cell stacks, wherein the heated coolant causes the subset of the fuel cell stacks to reach an operating temperature.
Inventor(s): Chellappa Balan of Mason OH (US) for the boeing company
IPC Code(s): B64D13/08, B64D27/355, H01M8/04014
CPC Code(s): B64D13/08
Abstract: an aircraft air management system comprises an air heat exchanger; an intercooler; and a conduit system connected to the air heat exchanger, the intercooler, and a fuel cell stack. heated air flows through the conduit system to the air heat exchanger. the air heat exchanger is configured to cool the heated air to form cooler air, wherein the cooler air flows from the air heat exchanger through the conduit system to the intercooler; and the intercooler is configured to cool the cooler air to form cooled air, wherein the cooled air flows from the intercooler through the conduit system to the fuel cell stack.
Inventor(s): Chellappa Balan of Mason OH (US) for the boeing company, Michael F. Stoia of Rancho Santa Margarita CA (US) for the boeing company, Charles Aguilar of Arlington VA (US) for the boeing company, Drew Christopher Hoffman of Signal Hill CA (US) for the boeing company, Luis Gonzalez of Los Angeles CA (US) for the boeing company, Daniel A. Watts of Seal Beach CA (US) for the boeing company
IPC Code(s): B64D37/04, B64D27/31, B64D27/355, B64D33/08, B64D37/20, B64D37/30, F17C9/00, H01M8/04007, H01M8/04082
CPC Code(s): B64D37/04
Abstract: an aircraft comprises a fuselage, wings connected to the fuselage, engines connected to the wings, and liquid hydrogen tanks. each engine in the engines comprises a nacelle, an electric motor within the nacelle, a fuel cell stack within the nacelle, and a nacelle heat exchanger within the nacelle that receives air flowing through an inlet in the nacelle. the liquid hydrogen tanks are configured to store liquid hydrogen, wherein the liquid hydrogen tanks extend along an outside of the fuselage and above the wings and below windows in the fuselage.
Inventor(s): Daniel A. Watts of Seal Beach CA (US) for the boeing company
IPC Code(s): B64D37/30, B64D37/34, F17C9/00, H01M8/04007, H01M8/04082, H01M8/04089, H01M8/0438, H01M8/04746, B64D27/355
CPC Code(s): B64D37/30
Abstract: an aircraft comprises a fuselage; wings; engines connected to the wings; a set of liquid hydrogen tanks; a vent located on the tail on the fuselage; a conduit system connecting the liquid hydrogen tanks to the vent; and a controller. the controller is configured to control the conduit system to remove gaseous hydrogen in the set of liquid hydrogen tanks to travel through the conduit system and exit at the vent in response to pressure in the set of liquid hydrogen tanks being greater than a specified tolerance.
20250058891. Fuel Cell Aircraft Thermal Management System_simplified_abstract_(the boeing company)
Inventor(s): Chellappa Balan of Mason OH (US) for the boeing company, Michael F. Stoia of Rancho Santa Margarita CA (US) for the boeing company, Charles Aguilar of Arlington VA (US) for the boeing company, Drew Christopher Hoffman of Signal Hill CA (US) for the boeing company
IPC Code(s): B64D37/34, B64D13/06, B64D13/08, B64D33/10, B64D37/04, B64D37/30, B64D41/00, F02C7/22, H01M8/04029
CPC Code(s): B64D37/34
Abstract: an aircraft thermal management system comprising a high temperature loop and a low temperature loop. the high temperature loop is configured to manage a temperature of a fuel cell stack in a nacelle using a nacelle heat exchanger. the low temperature loop is configured to cool a number of heat loads in a nacelle using a heat capacity of liquid hydrogen.
Inventor(s): Chellappa Balan of Mason OH (US) for the boeing company, Michael F. Stoia of Rancho Santa Margarita CA (US) for the boeing company, Charles Aguilar of Arlington VA (US) for the boeing company, Drew Christopher Hoffman of Signal Hill CA (US) for the boeing company
IPC Code(s): B64C3/36, F02K3/06
CPC Code(s): B64C3/36
Abstract: a heat exchanger system for an aircraft comprises nacelle having an inlet and an outlet, a nacelle heat exchanger within the nacelle, and a fan system within the nacelle. air flows into the nacelle through the inlet and out of the nacelle through the outlet. the nacelle heat exchanger is configured to transfer heat away from a coolant using the air in an airflow to the nacelle heat exchanger. the fan system is configured to increase the airflow to the nacelle heat exchanger.
Inventor(s): Christopher R. Shurilla of Palm Desert CA (US) for the boeing company, Zackary L. Endsley of Wailuku HI (US) for the boeing company, John C. Mooney of Makawao HI (US) for the boeing company, Steven Fulton Griffin of Kihei HI (US) for the boeing company, Alexander C. Klein of Bellevue WA (US) for the boeing company, Frederick Theodore Calkins of Renton WA (US) for the boeing company
IPC Code(s): F03G7/06
CPC Code(s): F03G7/06145
Abstract: a deployable panel is provided comprising a first subpanel, a second subpanel, and a shape memory alloy hinge connecting the subpanels. the shape memory alloy hinge enables the subpanels to move between a position in which the first and second subpanels are folded over each other and an unfolded position in response to an energy source that changes the shape of the shape memory alloy hinge, wherein the unfolded position is trained into the shape memory alloy hinge to ensure precise kinematic mating between the subpanels. shape memory alloy springs are connected to the first subpanel and respective tethers connect the shape memory alloy springs to the second subpanel. the shape memory alloy springs contract in response to a second energy source to pull the subpanels together via the tethers when the subpanels are in the unfolded position to produce a seamless, featureless surface of the deployable panel.
Inventor(s): Michael F. Stoia of Rancho Santa Margarita CA (US) for the boeing company, Jianping Tu of Walnut CA (US) for the boeing company, Arun Muley of San Pedro CA (US) for the boeing company, Richard C. Smith, III of Huntington Beach CA (US) for the boeing company, Kevin Javier Jui of Torrance CA (US) for the boeing company
IPC Code(s): F28D15/02, B64D33/08, F28D21/00, H01M8/04007, H01M8/10, H02K7/18, H05K7/20
CPC Code(s): F28D15/0266
Abstract: an aircraft cooling system comprises an evaporator, condenser, an accumulator, and a pump system. the evaporator is configured to cool a set of heat loads in an aircraft using a liquid. the liquid forms a vapor in response to cooling the set of heat loads. the condenser is configured to receive the vapor from the evaporator and cool the vapor in which cooling the vapor forms the liquid. the accumulator is configured to receive the liquid from the condenser and store the liquid. the pump system is configured to pump the liquid stored in the accumulator to the evaporator.
20250060258. THERMAL DETECTION ASSEMBLIES AND METHODS_simplified_abstract_(the boeing company)
Inventor(s): Brandon Parker Jamison of Ladson SC (US) for the boeing company, Michael Lloyd Sangwin of Everett WA (US) for the boeing company
IPC Code(s): G01K5/48, B64D45/00, G01K1/08
CPC Code(s): G01K5/48
Abstract: a thermal detection assembly includes a housing extending between a first end and a second end. the first end of the housing being operably coupled with a surface of a power system and the housing extending through a passage of the surface. the housing includes interior surfaces defining a cavity that has an opening proximate the second end of the housing. an indicator device is disposed within the cavity and is engaged with a thermal spring system. characteristics of the thermal spring system change responsive to being exposed to a temperature exceeding a designated threshold. the thermal spring system controls movement of the indicator device to move the indicator device from a first position to a second position responsive to the characteristics changing. a portion of the indicator device moves out of the cavity responsive to the thermal spring system moving the indicator device to the second position.
Inventor(s): Brendan Patrick Williams of Brisbane (AU) for the boeing company, Reece Alexander Clothier of Brisbane (AU) for the boeing company, Aaron McFadyen of Brisbane (AU) for the boeing company, Guilherme Froes Silva of Brisbane (AU) for the boeing company
IPC Code(s): G06Q10/0635, G06Q50/40
CPC Code(s): G06Q10/0635
Abstract: mid-air collision (mac) risk models and systems and methods for generating mac risk maps are disclosed. an example apparatus disclosed herein includes at least one processor circuit to determine a horizontal distance and a vertical distance between a grid location in an airspace and a point of a flight trajectory, the flight trajectory associated with an encounter event with respect to the grid location, determine a first overlap probability between (a) a first horizontal probability distribution corresponding to the grid location and (b) a second horizontal probability distribution corresponding to the point, the second horizontal probability distribution corresponding to the horizontal distance, determine a second overlap probability between (c) a first vertical probability distribution corresponding to the grid location and (d) a second vertical probability distribution corresponding to the point, the second vertical probability distribution corresponding to the vertical distance, determine, based on the first overlap probability and the second overlap probability, a risk metric corresponding to the grid location, and generate a risk map based on the risk metric.
Inventor(s): Chongman Whang of Lynnwood WA (US) for the boeing company, Linda L. Lin of Seal Beach CA (US) for the boeing company, Ephraim Mark De Dios Lapingcao of Everett WA (US) for the boeing company, Linette Sogin Whang of Costa Mesa CA (US) for the boeing company
IPC Code(s): G06Q30/0601
CPC Code(s): G06Q30/0621
Abstract: creating a customer layout configuration of a vehicle is provided. the method comprises pulling, from a customer database, a number of text documents that specify a customer's preferences for the layout configuration. technical requirements are determined according to a requirement database tool based on the customer preferences. functional data and logical data are determined according to a system architecture modeling tool based on the customer preferences. a physical layout model of the vehicle is generated according to the customer preferences in the text documents within constraints of the technical requirements, functional data, and logical data.
Inventor(s): John C. RYAN of Yorba Linda CA (US) for the boeing company
IPC Code(s): G06T7/20, G06T5/30
CPC Code(s): G06T7/20
Abstract: the present disclosure provides systems and techniques for image-based target detection and tracking. an example technique includes obtaining a geodetic motion-compensated integrated (gmci) output image of a target. an approximation to a matched filter is generated, based on information associated with the target. an enhanced image is generated based at least in part on the approximation and the gmci output image. the target is detected and tracked using the enhanced image.
Inventor(s): Maurice Masequesmay of Huntington Beach CA (US) for the boeing company, Kevin C. Hagen of North Kansas City MO (US) for the boeing company, Jonathan K. Lau of La Palma CA (US) for the boeing company
IPC Code(s): G06V20/13, G06T3/00, G06T7/38, G06V20/40
CPC Code(s): G06V20/13
Abstract: a computing device, method and computer program product are provided to identify a feature. in a method, images are captured at different points in time and space and a reference plane is defined in a reference frame. the method includes applying image warping to map a plurality of reference points of a respective image in a sensor plane to corresponding reference points of the reference plane and mapping pixel coordinates for a plurality of pixels of the reference plane to the respective image based upon a positional relationship between the reference plane and a representation of the respective image established by having applied image warping to the respective image. the method further includes interpolating from pixels of the respective image to pixels at the pixel coordinates of the reference plane to generate an interpolated representation of the respective image that is then used to identify the feature within the scene.
20250062667. TRANSVERSE FLUX ASYNCHRONOUS ELECTRIC MACHINE_simplified_abstract_(the boeing company)
Inventor(s): Jeremiah Vannest of Columbus OH (US) for the boeing company, Shengyi Liu of Sammamish WA (US) for the boeing company
IPC Code(s): H02K17/12, B64D27/35, H02K1/16, H02K1/24, H02K11/33
CPC Code(s): H02K17/12
Abstract: examples are disclosed that relate to an electric machine that achieves independent speed, variable frequency power generation and has increased power density, efficiency, reliability, and reduced complexity relative to conventional electric machines. in one example, an electric machine includes a stator, a first stationary winding coupled to the stator, a second stationary winding coupled to the stator, and a rotor. the second stationary winding includes a plurality of winding segments corresponding to a number of phases of power of the electric machine. the rotor extends through the stator and the second stationary winding. the rotor includes a plurality of rotor segments. each rotor segment of the plurality of rotor segments includes a plurality of pole lobes that extend radially from the rotor segment. two or more pole lobes of each rotor segment are located on opposing sides of a corresponding winding segment of the second stationary winding.
The Boeing Company patent applications on February 20th, 2025
- The Boeing Company
- B21D5/00
- B21D31/00
- CPC B21D5/004
- The boeing company
- B23B49/02
- CPC B23B49/023
- B26D7/32
- B64C1/06
- B64C1/14
- B64F5/10
- CPC B26D7/32
- B32B7/023
- B32B27/08
- B32B27/28
- B32B37/18
- CPC B32B7/023
- B32B38/18
- B32B5/12
- B32B38/00
- B32B41/00
- CPC B32B38/185
- B64C1/18
- B32B3/08
- B32B5/02
- B32B27/30
- B32B27/40
- B32B37/12
- CPC B64C1/18
- B64C1/40
- CPC B64C1/403
- B64D13/08
- B60L50/72
- B60L58/33
- B64D13/00
- H01M8/04007
- H01M8/04029
- CPC B64D13/08
- B64D27/355
- H01M8/04014
- B64D37/04
- B64D27/31
- B64D33/08
- B64D37/20
- B64D37/30
- F17C9/00
- H01M8/04082
- CPC B64D37/04
- B64D37/34
- H01M8/04089
- H01M8/0438
- H01M8/04746
- CPC B64D37/30
- B64D13/06
- B64D33/10
- B64D41/00
- F02C7/22
- CPC B64D37/34
- B64C3/36
- F02K3/06
- CPC B64C3/36
- F03G7/06
- CPC F03G7/06145
- F28D15/02
- F28D21/00
- H01M8/10
- H02K7/18
- H05K7/20
- CPC F28D15/0266
- G01K5/48
- B64D45/00
- G01K1/08
- CPC G01K5/48
- G06Q10/0635
- G06Q50/40
- CPC G06Q10/0635
- G06Q30/0601
- CPC G06Q30/0621
- G06T7/20
- G06T5/30
- CPC G06T7/20
- G06V20/13
- G06T3/00
- G06T7/38
- G06V20/40
- CPC G06V20/13
- H02K17/12
- B64D27/35
- H02K1/16
- H02K1/24
- H02K11/33
- CPC H02K17/12