The Boeing Company patent applications on December 26th, 2024
Patent Applications by The Boeing Company on December 26th, 2024
The Boeing Company: 19 patent applications
The Boeing Company has applied for patents in the areas of G06N20/00 (2), G05D1/00 (2), G08G5/00 (2), G05D109/20 (1), G01J5/90 (1) B23Q3/15503 (1), G01R31/367 (1), H01Q3/08 (1), H01L21/02167 (1), G08G5/0043 (1)
With keywords such as: aircraft, flight, target, layer, vehicle, include, surface, based, tool, and configured in patent application abstracts.
Patent Applications by The Boeing Company
20240424626. Automated Selection of Cutting Tools_simplified_abstract_(the boeing company)
Inventor(s): Justin Lee Peters of Carrollton IL (US) for the boeing company
IPC Code(s): B23Q3/155
CPC Code(s): B23Q3/15503
Abstract: a method of tool and parameter selection is presented. tap test data is generated for a machine by performing tap testing on the machine with a plurality of tools. geometric features of a part to be machined in a workpiece by the machine are extracted. the plurality of tools is filtered by applying a series of rules based on the geometric features of the part to identify a selected tool for a machining operation to form the part. in some illustrative examples, cutting parameters are set for the machining operation using the tap test data for the machine with the selected tool.
Inventor(s): Xiaoxi WANG of Mukilteo WA (US) for the boeing company, Jill Elisabeth SEEBERGH of Seattle WA (US) for the boeing company, Gary E. GEORGESON of Tacoma WA (US) for the boeing company
IPC Code(s): B29C33/38, B29C35/02, B29C35/04, B29L31/30
CPC Code(s): B29C33/3821
Abstract: a material system including a plurality of expandable pellets or a monolithic flexible carrier is disclosed, each of which may include a polymer matrix configured to hold an expandable core, and a flexible skin configured to encapsulate the polymer matrix, and where the flexible skin is at least partially permeable with respect to the expandable core or a gas released by the expandable core. implementations of the material system may include where the polymer matrix may include a thermoplastic polymer. the material system may include a charging source configured to introduce blowing agent. a method of curing a composite part is also described.
Inventor(s): Kariza T. Martin of Altona Meadows (AU) for the boeing company, Jason McBain of Werribee (AU) for the boeing company
IPC Code(s): B29C70/48, B29C70/44
CPC Code(s): B29C70/48
Abstract: a curing tool assembly for composite manufacturing includes a curing tool and a cover plate. the curing tool includes a tool surface that defines a resin channel. the cover plate overlays the resin channel. the cover plate defines openings in fluidic communication with the resin channel. the openings are arranged to provide different flow capacity through different portions of the cover plate along the channel axis. methods for composite manufacturing with the curing tool assembly are also disclosed. a system for composite manufacturing includes the curing tool, the cover plate, a fluid impervious layer and a differential pressure generator.
20240425172. Free Play Chatter Suppression_simplified_abstract_(the boeing company)
Inventor(s): Steven F. Griffin of Kihei HI (US) for the boeing company, Zackary L. Endsley of Kihei HI (US) for the boeing company
IPC Code(s): B64C9/02, F16F1/36
CPC Code(s): B64C9/02
Abstract: an apparatus and method for suppressing free play chatter of a control surface of an aircraft. the free play chatter suppression apparatus includes a containment vessel connected to a control surface of an aircraft. a lossy material is contained within the containment vessel. a body is positioned within the lossy material. the deceleration of the body by the lossy fluid is transmitted to the control surface to dampen vibrations of the control surface.
Inventor(s): Alan J. Wong of Issaquah WA (US) for the boeing company, Curtis John Call of Federal Way WA (US) for the boeing company, Theodore Carl Arnold of Sammamish WA (US) for the boeing company
IPC Code(s): B64D41/00, B64C1/16, B64D27/40
CPC Code(s): B64D41/00
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.
20240425199. VISION-BASED VEHICLE GUIDANCE_simplified_abstract_(the boeing company)
Inventor(s): Rongsheng Li of Hacienda Heights CA (US) for the boeing company, David K. Mefford of Huntsville AL (US) for the boeing company
IPC Code(s): B64F1/20, G05D1/04, G08G5/02
CPC Code(s): B64F1/20
Abstract: vision-based vehicle guidance is disclosed. an example landing pad for vision-based guidance of a vehicle includes a first perimeter of a landing area defined by the landing pad, the first perimeter having a first array of first light sources, and a second perimeter having a second array of second light sources, the second perimeter around the first perimeter, at least two of the first or second light sources having a different light characteristic to define a pattern to be detected by an image sensor of the vehicle for guiding the vehicle toward or away from the landing area.
Inventor(s): Monica Tatar of Bothell WA (US) for the boeing company
IPC Code(s): B64F5/10, G06F30/15, G06F113/28
CPC Code(s): B64F5/10
Abstract: a method for joining structures includes steps of: (1) fabricating a splice based on measurements of a first-structure surface of a first structure and a second-structure surface of a second structure along a joint formed between the first structure and the second structure; (2) installing the splice using a plurality of verification holes formed in the first structure, the second structure, and the splice; and (3) self-verifying that a gap between a splice surface of the splice and each one of the first-structure surface and the second-structure surface is less than or equal to a maximum allowable dimension of the gap by installing the splice.
Inventor(s): Leo H. Hui of Alhambra CA (US) for the boeing company, Haig F. Krikorian of Fullerton CA (US) for the boeing company, Chrysanthie D. Chamis of Palos Verdes Peninsula CA (US) for the boeing company
IPC Code(s): B64G1/24, G05D1/00, G05D1/10
CPC Code(s): B64G1/247
Abstract: an example method executed by a controller onboard a spacecraft generates a mission plan in real-time that guides the spacecraft along a space autonomous mission to rendezvous with two or more orbiting target objects. the method includes establishing potential permutations for all possible unique maneuver sequences in which to visit the two or more orbiting target objects, and for each potential permutation, determining a collision-free maneuver plan for defining orbit trajectories to intercept each of the two or more orbiting target objects for each of the possible unique maneuver sequences. an optimal permutation is determined that meets viewing constraints of the two or more orbiting target objects, a viewing priority, and fuel constraints of the spacecraft. a mission visit plan is generated using the optimal permutation, and the spacecraft executes the plan to rendezvous with and inspect the two or more orbiting target objects.
Inventor(s): Alejandro FRANSOY PEREIRA of A Coruña (ES) for the boeing company, José Ignacio VIDAL FRANCO of Santiago de Compostela (ES) for the boeing company, Ernesto VALLS HERNÁNDEZ of Madrid (ES) for the boeing company
IPC Code(s): B64U20/87, B64U10/25, G06N20/00
CPC Code(s): B64U20/87
Abstract: techniques for vehicle control are disclosed. these techniques include a collision trajectory prediction of an air vehicle and identifying an object below the uav using one or more sensors. the techniques further include determining a risk that the air vehicle will collide with the object should the vehicle later lose propulsion, and protecting against the air vehicle colliding with the object, based on the determined risk
Inventor(s): Joseph J. Kreitle of Summerville SC (US) for the boeing company
IPC Code(s): G01J5/08, G01J5/02, G01J5/53, G01J5/90
CPC Code(s): G01J5/0814
Abstract: a system and method for evaluating a burn test includes using an optical sensor system to detect an infrared reflection of a flame on a test piece and using a computer to capture initiation of fire damage to the test piece using the infrared reflection and to capture the fire damage though cessation of the fire damage using the infrared reflection.
Inventor(s): Lijun Gao of Renton WA (US) for the boeing company, Shengyi Liu of Seattle WA (US) for the boeing company, Glen M. Brown of Woodinville WA (US) for the boeing company
IPC Code(s): G01R31/367, G01R31/3828, G01R31/396
CPC Code(s): G01R31/367
Abstract: a system may include a battery and a processor configured to continuously record a voltage and current as a function of time. a time window may be determined based on the current as a function of time. during the time window, an accumulated electric charge may be substantially zero and an accumulated absolute value of the electric charge may substantially equal a stored comparison value. the processor may calculate an energy loss of the battery and a charge loss rate of the battery within the time window. the processor may further determine whether an internal short circuit exists within the battery based on the charge loss rate and a predetermined threshold value. in response to determining that the internal short circuit exists, the processor may generate an indication that the internal short circuit exists.
Inventor(s): Mark David McCabe of Larkspur CO (US) for the boeing company, Alexander Bellemare-Davis of Vancouver BC (CA) for the boeing company, Meng Xi Hu of Vancouver BC (CA) for the boeing company, Yun Chu of New Westminster BC (CA) for the boeing company, Tina Pan of Vancouver BC (CA) for the boeing company
IPC Code(s): G05D1/06, G05D1/00
CPC Code(s): G05D1/0688
Abstract: a system (for determining one or more emergency escape paths for one or more emergencies that can occur during a flight of an aircraft) includes a control unit configured to automatically determine the one or more emergency escape paths for the one or more emergencies based on performance capabilities of the aircraft, terrain within at least a portion of an original flight path or the one or more emergency escape paths, and obstacles within at least a portion of the original flight path or the one or more emergency escape paths.
Inventor(s): Chaitanya Pavan Kumar ARIPIRALA of Bangalore Karnataka (IN) for the boeing company, Veeresh Kumar Masaru NARASIMHULU of Bangalore Karnataka (IN) for the boeing company, Joost E. KOENNEN of Meppel (NL) for the boeing company, J. L. TYLEE of Seattle WA (US) for the boeing company
IPC Code(s): G05D1/654, G05D1/644, G05D109/20
CPC Code(s): G05D1/6545
Abstract: a system and a method for operating an aircraft during a descent phase of flight include a control unit configured to receive data regarding one or both of a current flight or one or more previous flights of the aircraft from one or more sensors of the aircraft. the control unit is further configured to determine efficient descent phase parameters for the aircraft based on the data. the aircraft is operated during the descent phase of one or both of the current flight or one or more future flights according to the efficient descent phase parameters.
Inventor(s): Willaredt Hardy of San Francisco CA (US) for the boeing company, Anthony W. Baker of Gilbertsville PA (US) for the boeing company, Philip Lawrence Freeman of Summerville SC (US) for the boeing company
IPC Code(s): G06T7/80, B41J29/393, G06T7/62, G06T7/73
CPC Code(s): G06T7/80
Abstract: the present application is directed for use with a printhead assembly that is mounted to a robot. one application provides a system for inkjet printing on large objects such as commercial aircraft surfaces. the application provides for calibrating a camera with relation to the motion of the robot. the calibration occurs is achieved using one or more calibration artifacts printed by the inkjet system.
Inventor(s): Maxim Constantijn VOS of Madrid (ES) for the boeing company, Daniel Ramiro REBOLLO of Madrid (ES) for the boeing company, David Rubio MOTA of Madrid (ES) for the boeing company
IPC Code(s): G08G5/00, B64D43/00
CPC Code(s): G08G5/0039
Abstract: techniques for aircraft flight management are disclosed. these techniques include receiving, at a flight management system (fms) of an aircraft, a target value, the target value including at least one of: (i) an altitude target value or (ii) a time target value. the techniques further include determining a target aircraft position relating to the target value, based on a trajectory for the aircraft. the techniques further include calculating a distance for the aircraft to travel from a current aircraft position to the target aircraft position and displaying the calculated distance in a user interface of the aircraft. the techniques further include providing coordinates for the target aircraft position to the fms for use in flight management of the aircraft.
Inventor(s): Kirk A. Vining of Renton WA (US) for the boeing company, Alvin L. Sipe of Kenmore WA (US) for the boeing company, Dragos D. Margineantu of Bellevue WA (US) for the boeing company
IPC Code(s): G08G5/00, G06N20/00
CPC Code(s): G08G5/0043
Abstract: a method of optimizing flights of a fleet of aircraft is provided. the method includes accessing flight plans for flights of a fleet of aircraft through an air transportation network, tracking positions and trajectories of one or more aircraft of the fleet that are currently in-flight, and applying the flight plans and the positions and trajectories to a reinforcement learning model configured to determine maneuvers that achieves a respective maximum cumulative value of an operational efficiency metric across the flights of the fleet of aircraft, one or more of the maneuvers constituting a deviation from a respective flight plan. a comparison of respective maximum cumulative values of the operational efficiency metric is performed for the aircraft of the fleet of aircraft, one of the aircraft is selected based on the comparison, and a notification of the deviation from the respective flight plan is sent to the one of the aircraft.
20240429041. FORMING A PLANAR SEMICONDUCTOR SURFACE_simplified_abstract_(the boeing company)
Inventor(s): Shanying Cui of Calabasas CA (US) for the boeing company, Samuel J. Whiteley of Venice CA (US) for the boeing company, Jason A. Graetz of Calabasas CA (US) for the boeing company, John J. Vajo of West Hills CA (US) for the boeing company, Adam E. Sorensen of Moorpark CA (US) for the boeing company
IPC Code(s): H01L21/02, H01L21/311
CPC Code(s): H01L21/02167
Abstract: a method for producing a planar semiconductor surface includes forming a workpiece that has a carrier substrate, one or more insulating layers, a semiconductor layer, a first etch stop layer, and a second etch stop layer; forming a contact on the workpiece; biasing the workpiece to a second voltage through the contact; etching the second etch stop layer and part of the first etch stop layer with a photo-electrochemical etching and the second voltage that selectively removes the second etch stop layer faster than the first etch stop layer; biasing the workpiece to a first voltage through the contact; and etching the first etch stop layer and part of the semiconductor layer with the photo-electrochemical etching and the first voltage that selectively removes the first etch stop layer faster than the semiconductor layer to produce a semiconductor device with a planar surface on the semiconductor layer.
Inventor(s): David Phillips of Seattle WA (US) for the boeing company
IPC Code(s): H01Q3/08, H01Q1/28
CPC Code(s): H01Q3/08
Abstract: systems, apparatus, and methods for calibration of satellite communication antennas are disclosed. an example aerial vehicle includes an antenna; an attitude sensor; machine-readable instructions; and programmable circuitry to at least one of instantiate or execute the machine readable instructions to at least identify a first angular position of the antenna associated with a peak power of a signal received by the antenna when the aerial vehicle is at a first heading; identify a second angular position of the antenna associated with a peak power of a signal received by the antenna when the aerial vehicle is at a second heading, the second heading different than the first heading; determine an offset between the attitude sensor and the antenna based on the first angular position and the second angular position; and cause a pointing angle of the antenna relative to an external source to be adjusted based on the offset.
Inventor(s): Robert A. Davis of Redmond WA (US) for the boeing company, Lawrence Britten Adamski of Marysville WA (US) for the boeing company, Jeffrey Robert Dempsey of Mount Pleasant SC (US) for the boeing company, Christopher Day of Shelton WA (US) for the boeing company, Travis Edward Dreyfoos of Tukwila WA (US) for the boeing company
IPC Code(s): H02G3/22, B60R16/02
CPC Code(s): H02G3/22
Abstract: the present disclosure includes a split ring wire bundle seal sleeve and an assembly technology for pressurized electrical feedthroughs. a kit of parts is also described.
The Boeing Company patent applications on December 26th, 2024
- The Boeing Company
- B23Q3/155
- CPC B23Q3/15503
- The boeing company
- B29C33/38
- B29C35/02
- B29C35/04
- B29L31/30
- CPC B29C33/3821
- B29C70/48
- B29C70/44
- CPC B29C70/48
- B64C9/02
- F16F1/36
- CPC B64C9/02
- B64D41/00
- B64C1/16
- B64D27/40
- CPC B64D41/00
- B64F1/20
- G05D1/04
- G08G5/02
- CPC B64F1/20
- B64F5/10
- G06F30/15
- G06F113/28
- CPC B64F5/10
- B64G1/24
- G05D1/00
- G05D1/10
- CPC B64G1/247
- B64U20/87
- B64U10/25
- G06N20/00
- CPC B64U20/87
- G01J5/08
- G01J5/02
- G01J5/53
- G01J5/90
- CPC G01J5/0814
- G01R31/367
- G01R31/3828
- G01R31/396
- CPC G01R31/367
- G05D1/06
- CPC G05D1/0688
- G05D1/654
- G05D1/644
- G05D109/20
- CPC G05D1/6545
- G06T7/80
- B41J29/393
- G06T7/62
- G06T7/73
- CPC G06T7/80
- G08G5/00
- B64D43/00
- CPC G08G5/0039
- CPC G08G5/0043
- H01L21/02
- H01L21/311
- CPC H01L21/02167
- H01Q3/08
- H01Q1/28
- CPC H01Q3/08
- H02G3/22
- B60R16/02
- CPC H02G3/22
