The Boeing Company patent applications on August 22nd, 2024
Patent Applications by The Boeing Company on August 22nd, 2024
The Boeing Company: 25 patent applications
The Boeing Company has applied for patents in the areas of B64D45/00 (3), G08G5/00 (2), B64U70/70 (2), B64C3/38 (2), B64U70/30 (2) B64C3/48 (2), B64U70/70 (2), B64D45/00 (2), A62C3/06 (1), B64D39/00 (1)
With keywords such as: end, assembly, data, vehicle, coupled, interface, mechanism, aircraft, position, and having in patent application abstracts.
Patent Applications by The Boeing Company
Inventor(s): Dalton W. Hamburg of Bothell WA (US) for the boeing company, Eric M. Chapman of Bonney Lake WA (US) for the boeing company
IPC Code(s): A62C3/06, A62C35/68, B09B3/00, B29C64/30, B33Y40/00
CPC Code(s): A62C3/06
Abstract: a flammable passivation apparatus includes a powder waste collection bin having a chamber in which a flammable powder can be filled. the apparatus also includes a fluid dispersion structure located in the chamber of the powder waste collection bin. the fluid dispersion structure is provided for enabling a passivation fluid to be dispersed throughout the chamber to passivate flammable powder contained in the chamber.
20240278417. PORTABLE TRAY AND INSTALLATION METHOD_simplified_abstract_(the boeing company)
Inventor(s): Peter Ray Smith of Suffolk VA (US) for the boeing company, Karl James Ettling of Ridgecrest CA (US) for the boeing company, Kenneth Alan Szarek of Beaufort SC (US) for the boeing company
IPC Code(s): B25H3/06
CPC Code(s): B25H3/06
Abstract: a tray used to support maintenance tools and service materials along an open bay in the side of a vehicle. the tray prevents these items from being damaged, or becoming foreign objects or debris that enter the open bay. the tray includes hanger assemblies that releasably attach the tray to bay door latches. adjustable length standoffs connect the tray to the side of the vehicle to support and prevent swaying of the tray.
20240278599. CASTER ASSEMBLIES HAVING CAM-OPERATED BRAKES_simplified_abstract_(the boeing company)
Inventor(s): Matthew James Frizzell of Ballwin MO (US) for the boeing company, Richard Kurt Wagner of Crestwood MO (US) for the boeing company, Joseph Edward Flach of St. Charles MO (US) for the boeing company
IPC Code(s): B60B33/02, B60B33/00
CPC Code(s): B60B33/021
Abstract: caster assemblies are disclosed herein. an example caster assembly includes a caster frame assembly including a caster frame, a caster mounting plate, and a brake arm; a pin having a first end and a second end opposite the first end, the second end to engage the brake arm; and a lever arm having a third end and a fourth end opposite the third end, the lever arm to pivot relative to the caster frame assembly between a first position and a second position, movement of the lever arm to the first position to cause the fourth end of the lever arm to actuate the pin in a first direction to move the brake arm to the engaged position to restrict rotation of the wheel.
Inventor(s): Emily Georgia Rayner of Newport (AU) for the boeing company, Benjamin Stanislaw Zielinski of Port Melbourne (AU) for the boeing company, Naram Abraham Faris of Port Melbourne (AU) for the boeing company, Timothy Trewern of Port Melbourne (AU) for the boeing company, Timothy Edward Mew of Brisbane City (AU) for the boeing company, Alana Jade Overmeyer of Port Melbourne (AU) for the boeing company, Jason Cochrane of Tecoma (AU) for the boeing company, Michael Hamilton of BRISBANE (AU) for the boeing company
IPC Code(s): B60D1/145, B60D1/01, B60D1/44, B60D1/64, B60D1/66
CPC Code(s): B60D1/145
Abstract: systems and methods for docking vehicles for towing are disclosed herein. an example docking system to mechanically couple a first vehicle and a second vehicle includes a first docking assembly and a second docking assembly. the first docking assembly includes a first mounting interface to be coupled to the first vehicle and a receiver rotatably coupled to the first mounting interface to enable the receiver to rotate about a pitch axis relative to the first vehicle. the receiver defines an opening. the second docking assembly includes a second mounting interface to be coupled to the second vehicle and a plug to be inserted into the opening of the receiver. the plug is rotatably coupled the second mounting interface to enable the plug to rotate about a yaw axis relative to the second vehicle and rotate about a roll axis relative to the second vehicle.
Inventor(s): Emily Georgia Rayner of Newport (AU) for the boeing company, Benjamin Stanislaw Zielinski of Port Melbourne (AU) for the boeing company, Naram Abraham Faris of Port Melbourne (AU) for the boeing company, Timothy Trewern of Port Melbourne (AU) for the boeing company, Timothy Edward Mew of Brisbane City (AU) for the boeing company, Alana Jade Overmeyer of Port Melbourne (AU) for the boeing company, Jason Cochrane of Tecoma (AU) for the boeing company, Michael Hamilton of Brisbane (AU) for the boeing company
IPC Code(s): B60D1/36, B60D1/64
CPC Code(s): B60D1/363
Abstract: systems and methods for docking vehicles for towing are disclosed herein. an example docking assembly for a vehicle includes a mounting interface to be coupled to the vehicle, an interface component rotatably coupled to the mounting interface at a joint defining an axis, the interface component to be coupled to a corresponding interface component on another vehicle, and a compliance mechanism. the compliance mechanism is operable between: a first mode in which the interface component is locked from rotating about the axis; a second mode in which the interface component is rotatable about the axis and biased to a central position; and a third mode in which the interface component is freely rotatable about the axis.
20240278899. SELF-CLOSING AND RESETTING LATCH_simplified_abstract_(the boeing company)
Inventor(s): Jonathan P. Boas of Glenolden PA (US) for the boeing company
IPC Code(s): B64C1/14, E05C19/14
CPC Code(s): B64C1/1461
Abstract: a self-closing and resetting latch is disclosed herein. an example apparatus includes a pawl having a protrusion, the pawl coupled to an over-center spring, the over-center spring connected to a frame of a cabin door, and a latch hook having a first recess to receive the protrusion of the pawl and a second recess to receive a latch pin when the cabin door closes.
Inventor(s): Robert E. Grip of Rancho Palos Verdes CA (US) for the boeing company, John J. Brown of Costa Mesa CA (US) for the boeing company, Nathaniel J. Noel of North Charleston SC (US) for the boeing company
IPC Code(s): B64C3/48, B64C3/14, B64C39/08
CPC Code(s): B64C3/18
Abstract: there is provided a variable radius assembly having a spindle, at least one variable radius guide member coupled to, and driven by, the spindle, and a tension member attached to the variable radius guide member. the tension member is configured to attach to at least one variable length structural member. the variable radius assembly further has at least one gear coupled to, and driven by, the spindle, and has at least one rotational power source coupled to the spindle, and configured to rotate the spindle. the variable radius guide member enables a tension member length change at a non-linear rate for a constant rate of rotation of the spindle, allowing the at least one variable length structural member to be braced by the tension member at an inclination angle to the at least one variable length structural member throughout a range of motion.
Inventor(s): Robert E. Grip of Rancho Palos Verdes CA (US) for the boeing company, Christopher K. Droney of Long Beach CA (US) for the boeing company, John C. Vassberg of Long Beach CA (US) for the boeing company, Dino L. Roman of Lake Forest CA (US) for the boeing company, John J. Brown of Costa Mesa CA (US) for the boeing company, Nathaniel J. Noel of North Charleston SC (US) for the boeing company, Charles Daniel Peyton of Summerville SC (US) for the boeing company
IPC Code(s): B64C1/26, B64C3/38
CPC Code(s): B64C3/48
Abstract: there is provided an expandable strut assembly for a wing of an aircraft, having a strut with a strut cross section with an airfoil shape, and the strut having an outboard end coupled to the wing, an inboard end coupled to a fuselage, and an elongate body, and having at least one shape transition assembly connected to the strut. each shape transition assembly is configured to transition the strut between a contracted position and an expanded position, and is configured to transition the strut cross section between a contracted airfoil shape and an expanded airfoil shape. each shape transition assembly has a shape transition mechanism attached to an interior of the strut. the shape transition mechanism includes fixed length structural members, and a drive mechanism of variable length structural member(s), includes an actuation mechanism connected to the shape transition mechanism, and an activation mechanism coupled to the actuation mechanism.
Inventor(s): Robert E. Grip of Rancho Palos Verdes CA (US) for the boeing company, John J. Brown of Costa Mesa CA (US) for the boeing company
IPC Code(s): B64C3/38, F16G13/20
CPC Code(s): B64C3/48
Abstract: there is provided an extendable compression chain system for extending a structure. the system includes a track assembly, a curved guide assembly, an extendable compression chain assembly, an actuation mechanism, and a mechanical power apparatus. the extendable compression chain assembly is configured to travel along the track assembly and to follow the curved portion of the track assembly, to move from a retracted position to an extended position, to extend the structure coupled to the extendable compression chain assembly. the extendable compression chain assembly includes a compression chain structure having a first end, a second end, and modules. the modules are movable between a rigid position and a collapsed position, as the compression chain structure follows the curved portion of the track assembly, and wraps around the curved guide assembly. the extendable compression chain assembly includes an actuation end fitting and a structure interface end fitting.
20240278905. Linear Actuator Driven Flap Mechanism_simplified_abstract_(the boeing company)
Inventor(s): Samuel L. Block of Bothell WA (US) for the boeing company, Kevin R. Tsai of Redmond WA (US) for the boeing company
IPC Code(s): B64C13/38, B64C3/18
CPC Code(s): B64C13/38
Abstract: a linear actuator driven flap mechanism for an aircraft wing is contained within a wing support and fairing of the aircraft wing. the rib frame of the flap mechanism is attached to the wingbox structure of the aircraft wing at a first and second point. the rib frame of the flap mechanism defines a width with a first and second web. a linear actuator and a motion linkage are positioned with the width between the first and second webs of the rib frame. the linear actuator is not mechanically driven rotary actuation or mechanically driven linear actuation. as a result of the compact construction, the flap mechanism can be employed in thinner, smaller aircraft wings being designed today.
Inventor(s): Erik Ivar Wiman of Everett WA (US) for the boeing company, Marat Denuski of Kenmore WA (US) for the boeing company
IPC Code(s): B64D11/02, B64D11/04
CPC Code(s): B64D11/02
Abstract: present aspects are directed to a protective moisture dam comprising a first and second retainer and a protective sleeve for preventing a moisture/fluid flow from progressing from an aircraft cabin monument floor to an adjoining compartment located beneath an aircraft cabin monument floor.
20240278921. MODULAR HEAT EXCHANGER SYSTEMS_simplified_abstract_(the boeing company)
Inventor(s): Ralph E. Chestine of Monroe WA (US) for the boeing company
IPC Code(s): B64D13/08
CPC Code(s): B64D13/08
Abstract: a heat exchanger system and method includes a securing frame, a heat transfer core having heat transfer panels removably secured to the securing frame, the heat transfer panels optionally including a plurality of segment modules coupled together, and one or more filter screens removably secured to the securing frame at one or both of an inlet end or an outlet end. the heat transfer core is disposed between the inlet end and the outlet end.
20240278924. Inlet Outer Barrel Segmented Attach Flange_simplified_abstract_(the boeing company)
Inventor(s): Jason Franklin Joel of North Charleston SC (US) for the boeing company, Robert Morrow of Summerville SC (US) for the boeing company
IPC Code(s): B64D33/02, B64D29/06
CPC Code(s): B64D33/02
Abstract: an engine nacelle inlet is provided. the inlet comprises an inner barrel having a leading edge and a trailing edge. a segmented attach flange is connected to an outer circumference of the trailing edge of the inner barrel, wherein the segmented attach flange comprises a number of discrete attach flange fittings. an outer barrel having a leading edge and a trailing edge surrounds the inner barrel. a number of attachment brackets connect the outer barrel to the segmented attach flange. each attachment bracket comprises two struts connected at a common point on the trailing edge of the outer barrel and connected at separate points on one of the attach flange fittings to form a truss. each attachment bracket is connected to a separate respective attach flange fitting.
Inventor(s): Daniel Michael O'Shea of Seattle WA (US) for the boeing company, Shawn M. Chamberlain of Federal Way WA (US) for the boeing company
IPC Code(s): B64D39/00, G05D1/10
CPC Code(s): B64D39/00
Abstract: a trajectory planning system for a refueling boom includes a human-machine interface (“hmi”) device and an electronic control unit (“ecu”). the hmi device outputs electronic control signals, in response to which the ecu performs a method. the ecu accesses a three-dimensional (“3d”) boundary model of the receiver and a 3d model of the boom. the ecu calculates a boom-to-receiver relative position using the models and sensor data, and a planned trajectory between a boom tip and a receptacle on the receiver. the trajectory is calculated using the boom-to-receiver relative position and predictive artificial potential fields. a point is found on a baseline trajectory farthest from a straight line between the receptacle and boom tip, which is recorded as a temporary goal. the planned trajectory avoids contact between the boom and receiver features. the ecu executes a control action using the planned trajectory.
Inventor(s): Sherwin Chunshek Li of Edmonds WA (US) for the boeing company, Ryan L. Pettit of Snohomish WA (US) for the boeing company, Bryan A. Lopez of Seattle WA (US) for the boeing company, Robert Erik Freeman of Seattle WA (US) for the boeing company, Melville D.W. McIntyre of Mercer Island WA (US) for the boeing company, Leonard J. Inderhees of Bothell WA (US) for the boeing company, Russell T. Bridgewater of Monroe WA (US) for the boeing company
IPC Code(s): B64D45/00, G01P13/02
CPC Code(s): B64D45/00
Abstract: a system and a method include air data sensors configured to detect one more characteristics of air surrounding an aircraft. at least three of the air data sensors differ in type. the air data sensors are configured to output air data. a flight control unit is in communication with the air data sensors. the flight control unit is configured to receive the air data from the air data sensors and control at least one aspect of the aircraft based on at least a portion of the air data. in at least one example, the flight control unit is further configured to vote in relation to the air data from the air data sensors.
20240278928. SYSTEM AND METHOD FOR PROCESSING PILOT REPORTS_simplified_abstract_(the boeing company)
Inventor(s): Jalja Nisha of Bengaluru (IN) for the boeing company, Umesh Hosamani of Bengaluru (IN) for the boeing company, Ganesh Shabadi of Bengaluru (IN) for the boeing company, Akshay Sankeshwari of Bengaluru (IN) for the boeing company
IPC Code(s): B64D45/00, G08G5/00, G10L15/08
CPC Code(s): B64D45/00
Abstract: a system and method are provided for processing a pilot report (pirep) for a flight in an aircraft. an audio voice message is received from a pilot, and inputs are received from one or more sensors associated with the aircraft. the audio voice message is converted to a text message, and the text message is parsed into one or more word/phrase snippets, wherein each of the one or more word/phrase snippets comprises one or more words and/or one or more phrases. a pirep template is populated with the one or more inputs and with a subset of the one or more word/phrase snippets, thereby creating a completed pirep. the completed pirep is then transmitted to one or more receiving entities outside the aircraft. a model trained by a machine learning algorithm may be used to determine a severity level and a suggested mitigation plan for the completed pirep.
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.
Inventor(s): Joseph M. Greene of Wallingford PA (US) for the boeing company
IPC Code(s): C23C8/30
CPC Code(s): C23C8/30
Abstract: methods and apparatus to case harden titanium alloys are disclosed. a disclosed example method for case hardening a substrate including titanium comprises providing the substrate to a chamber; evacuating the chamber to achieve a vacuum therein, heating the substrate, providing a process gas to the chamber to diffuse hydrogen and a case hardening addition into the substrate, and evacuating the chamber to cause at least a portion of the hydrogen to diffuse from the substrate.
Inventor(s): Samuel R. Goertz of Issaquah WA (US) for the boeing company, Barry A. Fetzer of Renton WA (US) for the boeing company
IPC Code(s): G01N29/265, G01N29/06, G01N29/11, G01N29/44
CPC Code(s): G01N29/265
Abstract: a method for associating test data for a part under test with an end item coordinate system includes acquiring scan data during a plurality of scans of at least a portion of the part of an end item along a predetermined path plan using an ultrasonic scanning device of a robot. robot location information associated with the scan data acquired during the plurality of scans is recorded. the robot location information is based on a robot coordinate system. the robot location information is translated to end item location information within the end item coordinate system based on at least three common reference points in the predetermined path plan, an electronic design model of the end item within the end item coordinate system, and the part. a non-destructive inspection (ndi) system for associating the test data with the end item coordinate system is also provided.
Inventor(s): Aravindan Krishnan of Bangalore (IN) for the boeing company, Nayan Maiti of West Bengal (IN) for the boeing company, Daamini Visaalaakshi of Bangalore (IN) for the boeing company, Kishora Shetty of Bangalore (IN) for the boeing company, Sijo Varghese of Bangalore (IN) for the boeing company, Jeffrey D. Poskin of Black Diamond WA (US) for the boeing company, Sharon F. Arroyo of Sammamish WA (US) for the boeing company, Gunnar C. Grosenick of Kirkland WA (US) for the boeing company
IPC Code(s): G05B19/18
CPC Code(s): G05B19/182
Abstract: nesting methods and computer-controlled machine tools for cutting one or more objects from a workpiece. the nesting methods aid in minimizing wasted material by assigning efficiently packed, nested locations for each object on the workpiece. the nesting methods assign locations in view of a predetermined stacking order of the objects, thereby preventing issues in subsequent manufacturing steps that would result from a substantial reordering of the objects.
20240280993. MACHINE AND PROCESS FOR ROTATING A VEHICLE_simplified_abstract_(the boeing company)
Inventor(s): Mark R. Morel of Edmonds WA (US) for the boeing company, Neil Zimmer of Orondo WA (US) for the boeing company, Tristan Flanzer of Seattle WA (US) for the boeing company
IPC Code(s): G05D1/08, B64D45/00
CPC Code(s): G05D1/0816
Abstract: a machine and process for control of rotation of a vehicle about an axis of the vehicle is shown. a flight control system includes control laws that control the rotation of the vehicle around the axis of the vehicle. an estimate is derived for an inertia about the axis. the estimated inertia is derived from sensed quantities of material in a component of the vehicle. an inertia gain schedule and filter are added to enhance, using the estimated inertia, the accuracy of the control laws that control the rotation of the vehicle around the axis of the vehicle.
Inventor(s): Bryan Williams Lilley of Austin TX (US) for the boeing company, Joseph Daniel Schaefer of Richmond Heights MO (US) for the boeing company, Matthew J. Molitor of O'Fallon MO (US) for the boeing company
IPC Code(s): G06F30/17, G01M5/00, G01N3/24
CPC Code(s): G06F30/17
Abstract: methods of designing a structure taking into account thermal loads are presented. a method to analyze thermal build-up in a joint is presented. physical testing between a first material and a second material is performed to determine physical data comprising at least one of stiffness, strain, load, and displacement. the physical data is analyzed. a closed form equation is generated based on the analysis to calculate the thermal build-up in the joint.
Inventor(s): Benjamin Jafek of Somerville MA (US) for aurora flight sciences corporation, a subsidiary of the boeing company, Samvruta Tumuluru of San Francisco CA (US) for aurora flight sciences corporation, a subsidiary of the boeing company
IPC Code(s): G06V10/20, G06F18/20, G06V10/75, G06V20/64
CPC Code(s): G06V10/255
Abstract: a method includes receiving a first image that is captured at a first time. the method also includes detecting a location of a first object in the first image. the method also includes determining a region of interest based at least partially upon the location of the first object in the first image. the method also includes receiving a second image that is captured at a second time. the method also includes identifying the region of interest in the second image. the method also includes detecting a location of a second object in a portion of the second image that is outside of the region of interest.
Inventor(s): Trevor J. BERGSTROM of Seattle WA (US) for the boeing company
IPC Code(s): G08G5/00
CPC Code(s): G08G5/003
Abstract: the present disclosure provides techniques for machine learning-based anomaly prediction. a set of flight data for a flight of an aircraft is accessed, and an embedding is generated by processing the set of flight data using an autoencoder machine learning model. a reconstruction error is generated based on the embedding using the autoencoder machine learning model. an anomaly measure is generated for the set of flight data by processing the embedding and the reconstruction error using an anomaly machine learning model. in response to determining that the anomaly measure satisfies one or more criteria, an alert is output.
Inventor(s): Mateus S. Daczko of Olympia WA (US) for the boeing company, Stephen J. Young of Seattle WA (US) for the boeing company
IPC Code(s): H04B7/0426, H04B7/06, H04W72/541, H04W72/56
CPC Code(s): H04B7/043
Abstract: examples are disclosed that relate to adaptively adjusting a radio frequency (rf) signal to suppress interference with radio operation of a prioritized rf system while maintaining radio operation of a non-prioritized rf system. in one example, a system includes an antenna array, a rf signal detection subsystem, and a signal-forming subsystem. the rf signal detection subsystem is configured to detect a prioritized rf signal in a prioritized rf spectrum band and determine an angle of arrival of the prioritized rf signal. the signal-forming subsystem is configured to output a non-prioritized rf signal based at least on the angle of arrival. a radiation null is formed along the angle of arrival in a radiation pattern of the non-prioritized rf signal. the signal-forming subsystem is configured to transmit the non-prioritized rf signal via the antenna array.
- The Boeing Company
- A62C3/06
- A62C35/68
- B09B3/00
- B29C64/30
- B33Y40/00
- CPC A62C3/06
- The boeing company
- B25H3/06
- CPC B25H3/06
- B60B33/02
- B60B33/00
- CPC B60B33/021
- B60D1/145
- B60D1/01
- B60D1/44
- B60D1/64
- B60D1/66
- CPC B60D1/145
- B60D1/36
- CPC B60D1/363
- B64C1/14
- E05C19/14
- CPC B64C1/1461
- B64C3/48
- B64C3/14
- B64C39/08
- CPC B64C3/18
- B64C1/26
- B64C3/38
- CPC B64C3/48
- F16G13/20
- B64C13/38
- B64C3/18
- CPC B64C13/38
- B64D11/02
- B64D11/04
- CPC B64D11/02
- B64D13/08
- CPC B64D13/08
- B64D33/02
- B64D29/06
- CPC B64D33/02
- B64D39/00
- G05D1/10
- CPC B64D39/00
- B64D45/00
- G01P13/02
- CPC B64D45/00
- G08G5/00
- G10L15/08
- B64U70/70
- B64U10/13
- B64U70/30
- CPC B64U70/70
- B60L53/00
- B64F1/36
- B64U10/14
- C23C8/30
- CPC C23C8/30
- G01N29/265
- G01N29/06
- G01N29/11
- G01N29/44
- CPC G01N29/265
- G05B19/18
- CPC G05B19/182
- G05D1/08
- CPC G05D1/0816
- G06F30/17
- G01M5/00
- G01N3/24
- CPC G06F30/17
- G06V10/20
- G06F18/20
- G06V10/75
- G06V20/64
- CPC G06V10/255
- Aurora flight sciences corporation, a subsidiary of the boeing company
- CPC G08G5/003
- H04B7/0426
- H04B7/06
- H04W72/541
- H04W72/56
- CPC H04B7/043
