The Boeing Company patent applications on August 8th, 2024
Patent Applications by The Boeing Company on August 8th, 2024
The Boeing Company: 20 patent applications
The Boeing Company has applied for patents in the areas of B64D45/00 (3), G01S17/58 (2), B64U70/70 (2), B64U70/30 (2), A46B11/06 (1) B64U70/70 (2), A46B11/063 (1), B64F5/60 (1), H01R43/0482 (1), G08G5/065 (1)
With keywords such as: engine, contact, aircraft, light, workpiece, layer, configured, laser, filtered, and member in patent application abstracts.
Patent Applications by The Boeing Company
Inventor(s): Harinder S. Oberoi of Snohomish WA (US) for the boeing company, Kevin Marion Barrick of Kingston WA (US) for the boeing company, Yuanxin Charles Hu of Newcastle WA (US) for the boeing company, Melissa Anne Johnson of Puyallup WA (US) for the boeing company, Laura Carolyn Foster of Brier WA (US) for the boeing company
IPC Code(s): A46B11/06, B05C1/06
CPC Code(s): A46B11/063
Abstract: a sealant application nozzle comprises a manifold with a incurvate face; bristles extending outward from the incurvate face; and channels within the manifold culminating in outlets exiting through the incurvate face to dispose sealant onto the incurvate face and base of the bristles.
20240261914. Adaptive Workpiece Support System_simplified_abstract_(the boeing company)
Inventor(s): Justin Lee Peters of Carrollton IL (US) for the boeing company, Stephen Lynn Farabee of Wentzville MO (US) for the boeing company
IPC Code(s): B23Q1/25
CPC Code(s): B23Q1/25
Abstract: an adaptive workpiece support system comprising a wear plate comprising a precision datum face and a plurality of tool holes, and accessories interactive with the plurality of tool holes of the wear plate to support, locate, and hold a workpiece against the wear plate for machining the workpiece. the plurality of tool holes is laid out in a grid and extending through the precision datum face, a thickness of the wear plate, and a backside face of the wear plate. the wear plate is configured to locate a workpiece relative to three axes of a machine.
Inventor(s): Matthew B. Moore of Edmonds WA (US) for the boeing company, Patrick B. Stone of Monroe WA (US) for the boeing company
IPC Code(s): B23Q11/00, B23Q1/01, B23Q1/03
CPC Code(s): B23Q11/0039
Abstract: a system for damping machine-induced vibration in a workpiece includes a plurality of workpiece holders to hold the workpiece in a work cell. the system also includes a machine tool located in the work cell. the machine tool performs a machining operation on the workpiece while the workpiece is held by the plurality of workpiece holders. the system further includes a damping apparatus coupled to the workpiece. the damping apparatus controls machine-induced vibrations in the workpiece during the machining operation.
Inventor(s): Darren Michael Chan of Thousand Oaks CA (US) for the boeing company, Wyatt Spalding McAllister of Santa Monica CA (US) for the boeing company, Heiko Hoffmann of Simi Valley CA (US) for the boeing company
IPC Code(s): B25J9/16, B25J11/00
CPC Code(s): B25J9/1697
Abstract: a method, apparatus, system, and computer program product for positions a wire contact. a sequence of images of a wire contact is generated while the wire contact moves from a first position to a second position. the sequence of images is generated by the camera system connected to the end effector and the wire contact is held by the end effector. edges are detected in the sequence of images to form edge images. background edges are removed from the edges in the edge images leaving contact edges in the edges for the wire contact to form a contact edge image. the wire contact is identified using the contact edges in the contact edge image. a pose of the wire contact is determined from the wire contact identified in the contact edge image.
Inventor(s): Nayeem Chowdhury of Melbourne (AU) for the boeing company
IPC Code(s): B29C65/00, B29C65/20, B29C65/30
CPC Code(s): B29C66/824
Abstract: a tacking element for tacking workpieces in composite manufacturing includes a base member, an actuating member and a heating member. the actuating member secured to the base member. the heating member disposed on the base member or the actuating member and configured to selectively radiate heat toward the actuating member. the actuating member is configured to transform from an inactive position to an active position in response to the heat from the heating member. a tacking stick and system that implements the tacking element is provided. a method for tacking workpieces in composite manufacturing is also provided.
20240262055. Integrated Caul with Elastomeric Seals_simplified_abstract_(the boeing company)
Inventor(s): Samuel Shane Brickey of Bellingham WA (US) for the boeing company, Julia Karolina Slusarski of Seattle WA (US) for the boeing company
IPC Code(s): B29C70/54, B29C70/44
CPC Code(s): B29C70/549
Abstract: a method, apparatus, and system for applying a vacuum-based pressure on an uncured composite structure. membranes are bonded to a boundary of a caul. the membranes include positive features that define vacuum channels. the membranes are spliced to each other. the positive features that define the vacuum channels in the membranes are aligned to each other during splicing of the membranes. the membranes spliced to each other and bonded to the caul to form an integrated caul. the integrated caul applies a pressure on the uncured composite structure during operation of the integrated caul.
Inventor(s): Andrew R. Tucker of Glendale MO (US) for the boeing company, David Conradi of St. Louis MO (US) for the boeing company
IPC Code(s): B64C1/40, B32B3/12, B32B3/26, B32B5/18, B32B7/12, B32B15/04
CPC Code(s): B64C1/40
Abstract: a thermal protection system is provided for a vehicle moving with velocity through a free stream of air. the system comprises a substrate layer having coolant feed holes through which coolant can pass, and an insulation layer bonded to the substrate layer and covering the coolant feed holes of the substrate layer. the system also comprises a honeycomb layer including (i) a first major surface bonded to the insulation layer, (ii) a second major surface opposite the first major surface and exposed to the free stream of air, and (iii) a cell structure that shifts a thermal boundary interface from between the insulation layer and the first major surface of the honeycomb layer to the second major surface of the honeycomb layer. surface cooling of the insulation layer and the substrate layer is provided by coolant passing through the coolant feed holes of the substrate layer into the insulation layer as the vehicle moves with velocity through the free stream of air.
20240262491. AUTOPILOT-BASED AIRCRAFT RECOVERY SYSTEM_simplified_abstract_(the boeing company)
Inventor(s): Rostyslav Svitelskyi of Shoreline WA (US) for the boeing company, Sherwin Chunshek Li of Edmonds WA (US) for the boeing company, Brian Kenyon Rupnik of Lake Stevens WA (US) for the boeing company
IPC Code(s): B64C13/18, B64C13/04, B64C13/22, B64D45/00
CPC Code(s): B64C13/18
Abstract: an aircraft includes an autopilot system including one or more processors. the one or more processors are configured to, in response to selection of an autopilot activation button during flight of the aircraft while the aircraft is operating in a first condition, apply first control laws to automatically control the flight of the aircraft. the one or more processors are further configured to, in response to selection of the autopilot activation button while the aircraft is operating in a second condition, apply second control laws to automatically control the flight of the aircraft, where the second control laws are different from the first control laws.
Inventor(s): Evelyn M. Matheson of Bothell WA (US) for the boeing company, Dorina L. Hester of Bothell WA (US) for the boeing company, Kolten Carrington Miller of Snoqualmie WA (US) for the boeing company, Eugene V. Solodovnik of Kenmore WA (US) for the boeing company, Shengyi Liu of Sammamish WA (US) for the boeing company, Kamiar Karimi of Kirkland WA (US) for the boeing company
IPC Code(s): B64D27/24, B64D31/00, H02K7/00, H02K7/18
CPC Code(s): B64D27/24
Abstract: one example provides a method for generating and using electric power in a hybrid power system for an aircraft. the hybrid power system has an engine and a high-voltage dc (hvdc) bus interconnecting a generator-motor system, an ac distribution system, and a dc distribution system. the method comprises operating the engine through a plurality of different operation phases. the method further comprises selectively providing, based on thrust demands of the engine, electric power from the hvdc bus to the generator-motor system to assist the engine in providing thrust. the method further comprises selectively extracting, using the engine driving the generator-motor system with a high-pressure spool (hps) shaft and/or a low-pressure spool (lps) shaft of the engine, electric power from the engine. the method further comprises selectively delivering the electric power extracted from the engine to the ac distribution system and/or the dc distribution system.
Inventor(s): Samantha A. Schwartz of Castle Pines CO (US) for the boeing company, Garoe Gonzalez of Frankfurt (DE) for the boeing company
IPC Code(s): B64D45/00, B64F1/00
CPC Code(s): B64D45/00
Abstract: a system and method for determining which engine of an aircraft to start first for a taxiing operation and/or for estimating a total amount of fuel needed by the aircraft for conducting the taxiing operation includes receiving or accessing historical fuel usage data for each of the first and second engines, receiving or accessing taxiway information, determining which of the first and second engines to start before the other based on optimizing one or more predetermined factors, and producing a first-to-start alert indicating which of the first and second engines is a first-to-start engine. an engine use plan may be determined, the total amount of fuel needed for executing the taxiing operation may be estimated, and a fuel-estimate indication may be produced.
Inventor(s): Peter J. Lake of Auburn WA (US) for the boeing company, Steven David Chapman of Chesterfield MO (US) for the boeing company, Jay Kevin McCullough of Belleville IL (US) for the boeing company
IPC Code(s): B64F5/60, B64D45/00
CPC Code(s): B64F5/60
Abstract: a method manages aircraft parts. a determination is made as to whether a no fault found parameter for a part type is greater than a no fault found threshold for an acceptable level for no fault found occurrences for the part type. the no fault found parameter is how often a no fault found for the part type occurs relative to how often that the part type has been removed and replaced. a determination is made as to whether an average fix time parameter is greater than a fix time threshold for a correct part replacement. the average fix time parameter identifies an average amount of time before a replaced part for the part type was replaced again. an alert is generated in response to the no fault found parameter being greater than the no fault found threshold and the average fix time parameter being greater than fix time threshold.
Inventor(s): Wayne Richard Howe of Irvine CA (US) for the boeing company, Terrance Mason of Pasadena CA (US) for the boeing company
IPC Code(s): B64U70/70, B64U10/13, B64U70/30
CPC Code(s): B64U70/70
Abstract: vertical takeoff and landing vehicles (vtols) of the type used for the point-to-point delivery and transport of payloads (e.g., packages, equipment, etc.) and personnel, are significantly stabilized at least during takeoff and landing with present aspects significantly ameliorating or significantly eliminating destabilizing effects, including ground effect, during vtol takeoff and/or landing.
Inventor(s): Wayne Richard Howe of Irvine CA (US) for the boeing company, Terrance Mason of Pasadena CA (US) for the boeing company
IPC Code(s): B64U70/70, B60L53/00, B64F1/36, B64U10/14, B64U70/30
CPC Code(s): B64U70/70
Abstract: vertical takeoff and landing vehicles (vtols) of the type used for the point-to-point delivery and transport of payloads (e.g., packages, equipment, etc.) and personnel, are significantly stabilized at least during takeoff and landing with present aspects significantly ameliorating or significantly eliminating destabilizing effects, including ground effect, during vtol takeoff and/or landing. vtol performance is further improved through the use of increased lift pressure and battery charging during takeoff.
20240262638. PICK-AND-PLACE SYSTEM AND METHOD_simplified_abstract_(the boeing company)
Inventor(s): Sandra L. Zmeu of Shoreline WA (US) for the boeing company, Jonathan Y. Ahn of Seattle WA (US) for the boeing company, Austin B. Ball of Seattle WA (US) for the boeing company, Ricardo A. Fritzke of Sammamish WA (US) for the boeing company, Christopher R. Brown of Seattle WA (US) for the boeing company
IPC Code(s): B65G47/90
CPC Code(s): B65G47/907
Abstract: a pick-and-place system includes a rigid elongate strongback, configured to be supported by a robotic arm of a robotic device. in addition, the pick-and-place system includes a plurality of actuator-clamp assemblies, mountable in spaced relation to each other on the strongback. each actuator-clamp assembly includes one or more jaw assemblies, each configured to clamp onto a localized segment of a workpiece. each actuator-clamp assembly also includes a multi-axis actuator, configured to couple the one or more jaw assemblies to the strongback and adjust an orientation of the localized segment prior to placement of the workpiece onto a mating structure.
Inventor(s): Nathan D. Hiller of Irvine CA (US) for the boeing company, Claudia E. Fritz-Thompson of Bothell WA (US) for the boeing company
IPC Code(s): G01P5/26, G01S17/58, G01S17/95
CPC Code(s): G01P5/26
Abstract: a method, apparatus, system, and computer program product for sensing air. a projected component of a laser radiation is emitted as a set of laser beams into an atmosphere from an aircraft. a backscatter light generated in response to said emitting the set of laser beams into the atmosphere is received to form a received backscatter light. the received backscatter light is filtered using a tunable optical filter system to form a filtered backscatter light. a control component derived from the laser radiation is filtered using the tunable optical filter system to form a filtered reference light. a set of parameters is determined for the aircraft using the filtered backscatter light and the filtered reference light.
20240264314. LIDAR OBJECT DETECTION SYSTEM_simplified_abstract_(the boeing company)
Inventor(s): Nathan D. Hiller of Irvine CA (US) for the boeing company, Claudia E. Fritz-Thompson of Bothell WA (US) for the boeing company
IPC Code(s): G01S17/933, G01S7/481, G01S17/04, G01S17/10, G01S17/58
CPC Code(s): G01S17/933
Abstract: a method, apparatus, system, and computer program product for detecting an object relative to a vehicle. a projected component of a laser radiation is emitted as a set of laser beams into an atmosphere from a vehicle. a backscatter light generated in response to said emitting the laser beam into the atmosphere is received to form a received backscatter light. the received backscatter light is filtered using a tunable optical filter system to form a filtered backscatter light. a control component derived from the laser radiation is filtered using the tunable optical filter system to form a filtered reference light. a set of parameters relating a presence of the object relative to the vehicle is determined using the filtered backscatter light and the filtered reference light.
Inventor(s): Vincent T. Raposas of Sewell NJ (US) for the boeing company, David G. Miller of Mount Laurel NJ (US) for the boeing company, Yi Lu of Media PA (US) for the boeing company
IPC Code(s): G06N3/049
CPC Code(s): G06N3/049
Abstract: methods and apparatus to identify, classify, and edit artificial spikes in cruise guide indicator (cgi) signal data are disclosed. an example apparatus includes memory, machine-readable instructions, and processor circuitry. the processor circuitry is to execute the machine-readable instructions to identify a spike in the cgi signal data. the processor circuitry is to execute the machine-readable instructions to determine whether the spike is an artificial spike. in response to determining that the spike is an artificial spike, the processor circuitry is to execute the machine-readable instructions to replace a portion of the cgi signal data including the artificial spike and a transient response of the artificial spike with edited cgi signal data.
Inventor(s): Martin Kearney-Fischer of Boston MA (US) for aurora flight sciences corporation, a subsidiary of the boeing company
IPC Code(s): G08G5/04, G05B13/02, G05D1/223, G05D1/46, G08G5/00
CPC Code(s): G08G5/045
Abstract: a method is provided for detecting and avoiding conflict along a current route of a robot. the method includes accessing or determining trajectories of the robot and a nearby moving object forward in time from their respective current positions, and detecting a conflict from a comparison of the trajectories. the method includes selecting a maneuver to avoid the conflict, and outputting an indication of the maneuver for use in at least one of guidance, navigation or control of the robot to avoid the conflict. selection of the maneuver includes determining a plurality of angles that describe the conflict such as those at which the robot and moving object observe one another, and/or an angle between their trajectories, and evaluating the plurality of angles to select the maneuver.
Inventor(s): Samantha A. Schwartz of Castle Pines CO (US) for the boeing company, Garoe Gonzalez of Frankfurt (DE) for the boeing company
IPC Code(s): G08G5/06, B64D43/00, G08G5/00
CPC Code(s): G08G5/065
Abstract: a system and method are provided for an aircraft at an airport surrounded by an environment, the aircraft having a first engine and a second engine wherein the second engine is to be started after the first engine. the system and method are configured for determining a minimum amount of warm-up time needed for starting the second engine to meet predetermined start-up requirements for the second engine, based on one or more of engine-related information relating to the second engine, aircraft-related information relating to the aircraft, airport-related information relating to the airport, and environment-related information relating to the environment, and producing an alert based on the minimum amount of warm-up time needed.
20240266795. WIRE TERMINATION SYSTEM_simplified_abstract_(the boeing company)
Inventor(s): Robert Arthur Nye of Land O Lakes FL (US) for the boeing company, Shawn David Mohlman of Mill Creek WA (US) for the boeing company, Matthew B. Knuth of Kirkland WA (US) for the boeing company, Joel Douglas Johnson of Everett WA (US) for the boeing company, Bradley J. Mitchell of Snohomish WA (US) for the boeing company, Eduardo Montero-Valdez of Lynnwood WA (US) for the boeing company, Ryan Cole of Freeland WA (US) for the boeing company, Ty Aaby Larsen of Proctor MN (US) for the boeing company
IPC Code(s): H01R43/048, H01R43/027
CPC Code(s): H01R43/0482
Abstract: an electrical contact system includes a contact having a barrel with a wire entry portion having a first diameter, a clip portion having a second diameter, and a cam portion having a second diameter at a first end that tapers to a third diameter at a second end near the wire entry portion. the system also includes a clip positioned in the clip portion of the barrel, wherein ends of inwardly directed tines of the clip are configured to engage the conductor to enable the clip to be drawn onto the cam portion in response to a user pulling the wire after insertion of the conductor through the clip.
20240267126. Motion Modulation to Communicate Information_simplified_abstract_(the boeing company)
Inventor(s): Wayne Richard Howe of Irvine CA (US) for the boeing company, Jeffrey H. Hunt of Thousand Oaks CA (US) for the boeing company
IPC Code(s): H04B10/50
CPC Code(s): H04B10/504
Abstract: a communications system comprising a laser generation system configured to emit a set of laser beams, a computer system, and a communications manager in the computer system. the communications manager is configured to identify digital information for transmission. the communications manager is configured to control an emission of the set of laser beams by the laser generation system to generate electromagnetic radiation with motions between positions in a space to thereby encode the digital information.
- The Boeing Company
- A46B11/06
- B05C1/06
- CPC A46B11/063
- The boeing company
- B23Q1/25
- CPC B23Q1/25
- B23Q11/00
- B23Q1/01
- B23Q1/03
- CPC B23Q11/0039
- B25J9/16
- B25J11/00
- CPC B25J9/1697
- B29C65/00
- B29C65/20
- B29C65/30
- CPC B29C66/824
- B29C70/54
- B29C70/44
- CPC B29C70/549
- B64C1/40
- B32B3/12
- B32B3/26
- B32B5/18
- B32B7/12
- B32B15/04
- CPC B64C1/40
- B64C13/18
- B64C13/04
- B64C13/22
- B64D45/00
- CPC B64C13/18
- B64D27/24
- B64D31/00
- H02K7/00
- H02K7/18
- CPC B64D27/24
- B64F1/00
- CPC B64D45/00
- B64F5/60
- CPC B64F5/60
- B64U70/70
- B64U10/13
- B64U70/30
- CPC B64U70/70
- B60L53/00
- B64F1/36
- B64U10/14
- B65G47/90
- CPC B65G47/907
- G01P5/26
- G01S17/58
- G01S17/95
- CPC G01P5/26
- G01S17/933
- G01S7/481
- G01S17/04
- G01S17/10
- CPC G01S17/933
- G06N3/049
- CPC G06N3/049
- G08G5/04
- G05B13/02
- G05D1/223
- G05D1/46
- G08G5/00
- CPC G08G5/045
- Aurora flight sciences corporation, a subsidiary of the boeing company
- G08G5/06
- B64D43/00
- CPC G08G5/065
- H01R43/048
- H01R43/027
- CPC H01R43/0482
- H04B10/50
- CPC H04B10/504
