The Boeing Company patent applications on September 19th, 2024
Patent Applications by The Boeing Company on September 19th, 2024
The Boeing Company: 22 patent applications
The Boeing Company has applied for patents in the areas of B25J15/00 (2), E05D3/06 (2), E05F15/53 (2), E05F5/00 (2), G08G5/00 (2) E05D3/06 (2), B25J15/009 (1), G06F9/546 (1), H01Q7/08 (1), H01Q1/288 (1)
With keywords such as: plate, nut, hinge, assembly, door, include, duct, aircraft, material, and configured in patent application abstracts.
Patent Applications by The Boeing Company
20240308089. NUT PLATE GRIPPERS AND RELATED METHODS_simplified_abstract_(the boeing company)
Inventor(s): Jason Cochrane of Melbourne (AU) for the boeing company
IPC Code(s): B25J15/00
CPC Code(s): B25J15/009
Abstract: nut plate grippers and related methods are disclosed herein. the nut plate grippers are configured to grip a nut plate along an engagement axis. the nut plate includes a base plate and a nut that is operatively attached to the base plate and defines a threaded central opening. the nut plate grippers include an attachment region, which is configured to facilitate attachment of the nut plate gripper to an end effector, an elongate resilient retention structure, which extends from the attachment region along the engagement axis and is sized for an interference fit within the threaded central opening, and a pair of orienting structures positioned on opposed sides of the elongate resilient retention structure and configured to operatively engage the base plate when the nut plate gripper grips the nut plate to precisely orient the base plate relative to the nut plate gripper along an orienting axis.
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
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): Eric Carlton Anderson of North Charleston SC (US) for the boeing company, Allen James Halbritter of Summerville SC (US) for the boeing company, Daniel Johnson of Charleston SC (US) for the boeing company, Adam Lee of Moncks Corner SC (US) for the boeing company, Luis Velasquez of Ladson SC (US) for the boeing company
IPC Code(s): B29C70/54, B25J15/00, B29C70/34, B29C70/44
CPC Code(s): B29C70/543
Abstract: embodiments include apparatus for compacting an object onto a rigid tool by applying a negative pressure while the scroll of material overlays the object. the apparatus comprises one or more spindles and a scroll of material that is stored on the one or more spindles. the scroll of material comprises a permeable layer and an impermeable membrane wherein the impermeable membrane contacts the permeable layer and may extend beyond a perimeter of the permeable layer.
Inventor(s): Edward Greene of Charleston SC (US) for the boeing company, Stephanie Metting of Seattle WA (US) for the boeing company, Jason Drexler of Edmonds WA (US) for the boeing company, Lloyd Layton Womack, II of Kirkland WA (US) for the boeing company, Anilegna Nunez Abreu of Lynnwood WA (US) for the boeing company
IPC Code(s): B41J2/045
CPC Code(s): B41J2/04503
Abstract: a method and system include controlling, by a control unit, a printer to form one or more tactile features on a surface of a component. said controlling includes varying a speed of a print head of the printer to vary one or more attributes of the one or more tactile features. in at least one example, said varying the speed includes varying the speed of the print head of the printer during a single pass of the print head in relation to the surface of the component.
20240308645. Inlet Cover Mechanism_simplified_abstract_(the boeing company)
Inventor(s): Keith Ryan Hollen of Saint Charles MO (US) for the boeing company, Bryan Michael Loris of Saint Charles MO (US) for the boeing company, Nathan Matthew Knibb of Manchester MO (US) for the boeing company, Everett Ryan Eaton of Saint Charles MO (US) for the boeing company, Michael L. Oleshchuk of Saint Charles MO (US) for the boeing company
IPC Code(s): B64C7/00, B64F5/10
CPC Code(s): B64C7/00
Abstract: an inlet cover mechanism for an air launched vehicle includes a quick release pin, a chassis, a collar, and a piston pin. the inlet cover mechanism facilitates attachment and deployment of an inlet cover with the air launched vehicle. the quick release pin is connected to the inlet cover. the chassis is connected to the air launched vehicle. the collar is connected to the chassis and is releasably engageable with the quick release pin. the piston pin is slidably engaged within the chassis and is configured to contact the quick release pin.
Inventor(s): Christopher J. HEIBERG of Sunset Beach CA (US) for the boeing company
IPC Code(s): B64G1/24, B64G1/28
CPC Code(s): B64G1/244
Abstract: systems and methods disclosed provide for attitude control of a body, the body including a plurality of thrusters and a plurality of gimballed rotors. operations performed include: receiving a command vector representing a desired torque on the body, generating a jacobian matrix that, when applied to a combined gimbal rate and thrust command vector, generates the command vector, generating components of a weighted pseudo inverse of the jacobian matrix and using the components with the command vector in order to generate the combined gimbal rate and thrust command vector. generating components of the weighted pseudo inverse of the jacobian matrix can include generating a weighting matrix including a plurality of diagonal elements, the plurality of diagonal elements representing at least the plurality of gimballed rotors and the plurality of thrusters.
Inventor(s): James Ivan MARDEL of Acton (AU) for the boeing company, Ivan Stewart COLE of Acton (AU) for the boeing company, Paul Andrew WHITE of Acton (AU) for the boeing company, Anthony Ewart HUGHES of Acton (AU) for the boeing company, Tracey Anne MARKLEY of Acton (AU) for the boeing company, Timothy Graham HARVEY of Acton (AU) for the boeing company, Joseph OSBORNE of Seattle WA (US) for the boeing company, Erik SAPPER of Seattle WA (US) for the boeing company
IPC Code(s): C09D5/08, B05D7/14, B05D7/24, B05D7/26, C07F3/06, C08K5/56, C09K15/32
CPC Code(s): C09D5/086
Abstract: the present disclosure is directed to processes, compositions and agents for inhibiting corrosion in various substrates, for example metal substrates. the present disclosure is also directed to corrosion inhibitors comprising organometallic polymers such as metal-organic frameworks (mofs), including compositions and processes comprising mofs for inhibiting corrosion in metal substrates.
Inventor(s): Michael T. Mortland of Mukilteo WA (US) for the boeing company
IPC Code(s): E05D3/06, E05F5/00, E05F15/53
CPC Code(s): E05D3/06
Abstract: an articulated hinge assembly for connecting a door to a fuselage of an aircraft includes an articulated hinge arm having a first hinge member pivotably coupled to a second hinge member at an elbow. the first hinge member includes a fuselage fitting pivotably coupled to a fuselage bracket. the second hinge member includes a door fitting pivotably coupled to a door bracket of the door. the articulated hinge assembly includes a linkage assembly coupled to the articulated hinge arm, the fuselage fitting and the door fitting. the linkage assembly includes a hinge linkage assembly coupled to the articulated hinge arm and the fuselage fitting and controlling movement of the hinge members relative to each other and relative to the fuselage fitting. the linkage assembly includes a door linkage assembly coupled to the articulated hinge arm and the door to control positioning of the door between open and closed positions.
Inventor(s): Michael T. Mortland of Mukilteo WA (US) for the boeing company
IPC Code(s): E05D3/06, E05F5/00, E05F15/53
CPC Code(s): E05D3/06
Abstract: an articulated hinge assembly for connecting a door to a fuselage of an aircraft includes an articulated hinge arm having a first hinge member pivotably coupled to a second hinge member at an elbow. a fuselage fitting is pivotably coupled to a fuselage bracket and a door fitting is pivotably coupled to a door bracket of the door. the articulated hinge arm is movable from a collapsed position to an expanded position to move the door from a door closed position to a door open position. the articulated hinge assembly includes a linkage assembly coupled to the articulated hinge arm, the fuselage fitting and the door fitting controlling movement of the first hinge member and the second hinge member relative to each other and relative to the fuselage fitting. the linkage assembly controls positioning of the door.
Inventor(s): Benjamin S. Zielinski of Melbourne (AU) for the boeing company, Jason Cochrane of Melbourne (AU) for the boeing company, Ashkan Amirsadri of Melbourne (AU) for the boeing company, Andre D. Swart of AI Ain (AE) for the boeing company
IPC Code(s): F16B37/04
CPC Code(s): F16B37/044
Abstract: nut plate grippers, end effectors that include nut plate grippers, robots that include end effectors, installation systems that include robots, and related methods are disclosed herein. the nut plate grippers are configured to grip a nut plate and include an attachment region, a first resilient projecting region, and a second resilient projecting region. the first resilient projecting region extends from the attachment region and defines a first nut plate-contacting end. the second resilient projecting region extends from the attachment region and defines a second nut plate-contacting end. the first resilient projecting region and the second resilient projecting region are configured to resiliently deflect toward one another to facilitate insertion of the first nut plate-contacting end and the second nut plate-contacting end between a pair of opposed plate flanges of a base plate of the nut plate. the methods include methods of gripping a nut plate utilizing the nut plate grippers.
Inventor(s): Nathan Otenti of Brighton MA (US) for aurora flight sciences corporation, a subsidiary of the boeing company, Joseph Chung of Cambridge MA (US) for aurora flight sciences corporation, a subsidiary of the boeing company, Jeffery Saunders of Quincy MA (US) for aurora flight sciences corporation, a subsidiary of the boeing company
IPC Code(s): G01C21/00, G05D1/46, G06F17/16, G06F18/232, G06V20/13
CPC Code(s): G01C21/3826
Abstract: a method of supporting robot(s) landing within a ground region is provided. the method includes accessing a map in which the ground region is tessellated into cells covering respective areas of the ground region. each cell is classified as feasible to indicate a respective area is feasible for landing, or infeasible to indicate the respective area is infeasible for landing. the map is searched for clusters of adjoining cells that are classified as feasible, covering clusters of adjoining areas that define sub-regions within the ground region that are feasible for landing. the sub-regions are ranked according to a cost metric, and one of the sub-regions is selected according to the ranking. a geographic position of the selected sub-region is then output for use in at least one of guidance, navigation or control of the robot(s) to land at the selected sub-region within the ground region.
Inventor(s): Morteza SAFAI of Newcastle WA (US) for the boeing company
IPC Code(s): G01N23/18, G01N23/04, G01N23/083
CPC Code(s): G01N23/18
Abstract: a system for radiographic inspection includes a line source that emits a fan shaped beam of x-rays and a linear x-ray detector that detects the fan shaped beam of x-rays. the system further includes a first movable platform that positions the line source to emit the fan shaped beam of x-rays towards the linear x-ray detector. a second movable platform positions the linear x-ray detector to detect the fan shaped beam of x-rays after transmission through the structure or component being inspected. synchronized movement of the first movable platform and the second movable platform significantly reduces the time of inspection while the fan shaped beam of x-rays minimizes health risks. the system further includes a first filter that blocks x-rays below a first energy threshold, and a second filter that blocks x-rays below a second energy threshold. the filters provide the system the ability to inspect structures and components formed of multiple types of materials, for example, foreign object debris.
Inventor(s): Rongsheng Li of Hacienda Heights CA (US) for the boeing company, Kenneth Cecil Clark of Jupiter FL (US) for the boeing company, Andrey Tolstov of Hohenkirchen- Siegertsbrunn (DE) for the boeing company, Tung-Ching Tsao of Torrance CA (US) for the boeing company, Cody L. Gruebele of Corona CA (US) for the boeing company, Chang Jin Yoo of Anaheim CA (US) for the boeing company
IPC Code(s): G01S19/45, G01S19/24
CPC Code(s): G01S19/45
Abstract: methods and apparatus to reduce communications for position, navigation and timing (pnt) determinations are disclosed. a disclosed example apparatus to enable pnt determination for a mobile station includes at least one memory, machine readable instructions, and processor circuitry to at least one of instantiate or execute the machine readable instructions to identify features of signals of opportunity (soop) measured at a reference station, generate a model based on the identified features of the soop in conjunction with a position and a timing of the reference station, and provide at least one of the model or parameters associated with the model to the mobile station for the pnt determination.
Inventor(s): Ronald J. Koontz of Mesa AZ (US) for the boeing company, Jason Ellis Sherrill of Mesa AZ (US) for the boeing company, Hyunsuk Shin of Los Angeles CA (US) for the boeing company, Sean M. Ramey of Stevens Lake WA (US) for the boeing company, Joshua R. Byrne of Seattle WA (US) for the boeing company, David C. Matthews of Duvall WA (US) for the boeing company
IPC Code(s): G06F9/38, G06F9/30
CPC Code(s): G06F9/3869
Abstract: a system, method and computer program product to synchronize processing across multiple lanes. in a system, a synchronizing interface network controller (sinc) communicates with a plurality of processors. each processor executes an application having thread(s) of operation. each processor notifies the sinc when a specific thread is ready to perform a respective operation. the sinc releases the processors to perform the respective operation upon being notified by all processors that the specific thread is ready to perform the respective operation. each processor is configured to monitor for the release of the processors and to also determine whether sufficient time remains within a time window to perform the respective operation. if insufficient time remains, a processor notifies the sinc that the specific thread is no longer ready to perform the respective operation. if the processors are released by the sinc while sufficient time remains, each processor performs the respective operation.
Inventor(s): Ronald J. Koontz of Mesa AZ (US) for the boeing company, Jason Ellis Sherrill of Mesa AZ (US) for the boeing company, Hyunsuk Shin of Los Angeles CA (US) for the boeing company
IPC Code(s): G06F9/54
CPC Code(s): G06F9/546
Abstract: a system and method are provided to synchronize communication between a synchronizing interface network controller (sinc) and two or more processors. each processor defines a plurality of user partitions. each user partition includes dedicated memory space associated with a software application executed by the respective processor. the sinc is configured to synchronously and directly push a message to one or more user partitions associated with the software applications that are being concurrently executed by the two or more processors. the one or more user partitions being executed by the two or more processors receive the same message. the one or more user partitions being executed by the two or more processors and associated with identical software applications are configured to synchronously and directly transmit a message to the sinc. the sinc receives the same message from one or more user partitions being concurrently executed by the two or more processors.
Inventor(s): Anker Benjamin Anderson of Mill Creek WA (US) for the boeing company, Nicholas Alexander Jones of Lynnwood WA (US) for the boeing company, Adam Matthew Miller Jensen of Lynnwood WA (US) for the boeing company, Sibi Radhakrishnan of Everett WA (US) for the boeing company
IPC Code(s): G06F30/12, G06F30/17, G06F30/18
CPC Code(s): G06F30/12
Abstract: improved duct modeling using an improved duct definition interface includes receiving, from an automated duct definition interface, a plurality of duct definition parameters associated with a duct; in response to the receiving, building a duct definition database based at least on the plurality of duct definition parameters, the duct definition database further comprising a plurality of operational parameters associated with the duct; generating a duct model associated with the duct based at least on the duct definition database; and communicating the duct model to a duct modeling application for rendering.
20240311728. AIRCRAFT CONGESTION REDUCTION AT AIRPORT_simplified_abstract_(the boeing company)
Inventor(s): Umesh Kallappa Hosamani of Bangalore (IN) for the boeing company, Akshay Arun Sankeshwari of Bengaluru (IN) for the boeing company, Ajaya Srikanta Bharadwaja of Bangalore (IN) for the boeing company, Veeresh Kumar Masaru Narasimhulu of Bangalore (IN) for the boeing company
IPC Code(s): G06Q10/0633, G06Q10/04, G06Q50/30
CPC Code(s): G06Q10/0633
Abstract: a system for aircraft congestion reduction on a ground at an airport includes a database, a computer, and a transmitter. the database is operational to store collected data gathered over at least a year at the airport. the computer is in communication with the database and is operational to train a machine learning model using the collected data, receive input data approximate a current time, and generate at the current time, based on the input data, the machine learning model, and a plurality of current aircraft, an estimated taxi time for a particular aircraft to move between an assigned gate and an assigned runway via an assigned route along the taxiways. the transmitter is in communication with the computer and is operational to transfer the estimated taxi time to the particular aircraft and a control center.
Inventor(s): Paul A. van Tulder of Burien WA (US) for the boeing company
IPC Code(s): G08G5/00
CPC Code(s): G08G5/0047
Abstract: a method, apparatus, system, and computer program product for managing a trajectory for an aircraft. a computer system receives an agreed trajectory change for a future portion of the trajectory for the aircraft. the strategic trajectory message is approved by a strategic air traffic controller. the computer system determines whether the agreed trajectory change has been received within a strategic time horizon for making strategic changes to the trajectory. the computer system sends the agreed trajectory change for a future portion of the trajectory for the aircraft to an aircraft computer system in the aircraft in response to the agreed trajectory change being received within the strategic time horizon.
20240312352. DYNAMIC APPROACH PROCEDURE SYSTEM_simplified_abstract_(the boeing company)
Inventor(s): Jordan Timothy Meek of Portland ME (US) for the boeing company, Charles E. Gehin-Scott of Belfast ME (US) for the boeing company
IPC Code(s): G08G5/02, G06F3/0482, G06F3/0484, G06T11/00, G08G5/00
CPC Code(s): G08G5/025
Abstract: a method and apparatus dynamically update customized integrated terminal approach procedure interfaces based on changing real-time events associated with aircraft and airports. a dynamic approach procedures application extracts and analyzes terminal approach data, aircraft data, airport data and real-time weather data to automatically generate an integrated terminal approach interface. the integrated terminal approach interface presents dynamic digital approach information, the interface including a map interface and a procedure side bar displaying route-related procedures data to assist pilots with selecting a route into the destination airport. as conditions change, displayed terminal approach data within the map and procedure side bar is updated and route recommendations are refined, to assist a user in selecting destination airports, routes, and relevant approach procedures.
20240312754. Composite Electron Beam Vacuum Tube_simplified_abstract_(the boeing company)
Inventor(s): Michael K. Strahan of Ogden UT (US) for the boeing company, Kyle Eversole of Ogden UT (US) for the boeing company
IPC Code(s): H01J35/06, H01J19/44, H01J23/07
CPC Code(s): H01J35/06
Abstract: an electron beam vacuum tube assembly is provides. the electron beam vacuum tube assembly comprises an anode assembly and a cathode assembly. a composite insulator tube provides electrical isolation between the anode assembly and cathode assembly, wherein the anode assembly, cathode assembly, and composite insulator are detachably connected each other.
20240313393. REFLECTOR ANTENNAS AND RELATED METHODS_simplified_abstract_(the boeing company)
Inventor(s): James Timothy Barrett of Playa Del Rey CA (US) for the boeing company
IPC Code(s): H01Q1/28, H01Q1/08, H01Q15/16
CPC Code(s): H01Q1/288
Abstract: reflector antennas and related methods are disclosed. an example antenna includes a hub; ribs coupled to the hub; a reflective material; gold-plated clips to couple the reflective material to respective ones of the ribs; and an actuator to cause respective ones of the ribs to move relative to the hub from a folded position to an unfolded position to expand the reflective material.
Inventor(s): John Dalton Williams of Decatur AL (US) for the boeing company, Michael F. Mitchell of Madison AL (US) for the boeing company, Timothy Doyle Messer of Huntsville AL (US) for the boeing company, Allon Joseph Stern of Leesburg VA (US) for the boeing company
IPC Code(s): H01Q7/08, H01Q1/38
CPC Code(s): H01Q7/08
Abstract: a very low frequency (vlf) receiver is provided. the vlf receiver comprises a magnetometer that detects a magnetic field, wherein the magnetometer comprises a rubidium gas cell. processing circuitry receives an electrical signal representative of vlf electromagnetic signals detected by the magnetometer. a multi-axis array encloses the magnetometer. the multi-axis array comprises a number of inductive coils. a closed loop current controller is connected to the inductive coils and runs on the processing circuitry. the closed loop current controller controls the magnetic field strength of the inductive coils to maintain a uniform magnetic field across the rubidium gas cell to allow the processing circuitry to detect the vlf electromagnetic signals.
20240313416. REFLECTOR ANTENNAS AND RELATED METHODS_simplified_abstract_(the boeing company)
Inventor(s): James Timothy Barrett of Playa Del Rey CA (US) for the boeing company
IPC Code(s): H01Q15/16, H01Q1/28
CPC Code(s): H01Q15/161
Abstract: reflector antennas and related methods are disclosed. an example antenna includes a base; a first rib and a second rib, the first rib and the second rib moveable relative to the base; a reflective material carried by the first rib and the second rib, the first rib, the second rib, and the reflective material to define a reflector portion of the antenna; and a gold-plated clip to couple a portion of the reflective material to the first rib.
The Boeing Company patent applications on September 19th, 2024
- The Boeing Company
- B25J15/00
- CPC B25J15/009
- The boeing company
- B29C33/38
- B29C35/02
- B29C35/04
- CPC B29C33/3821
- B29C70/54
- B29C70/34
- B29C70/44
- CPC B29C70/543
- B41J2/045
- CPC B41J2/04503
- B64C7/00
- B64F5/10
- CPC B64C7/00
- B64G1/24
- B64G1/28
- CPC B64G1/244
- C09D5/08
- B05D7/14
- B05D7/24
- B05D7/26
- C07F3/06
- C08K5/56
- C09K15/32
- CPC C09D5/086
- E05D3/06
- E05F5/00
- E05F15/53
- CPC E05D3/06
- F16B37/04
- CPC F16B37/044
- G01C21/00
- G05D1/46
- G06F17/16
- G06F18/232
- G06V20/13
- CPC G01C21/3826
- Aurora flight sciences corporation, a subsidiary of the boeing company
- G01N23/18
- G01N23/04
- G01N23/083
- CPC G01N23/18
- G01S19/45
- G01S19/24
- CPC G01S19/45
- G06F9/38
- G06F9/30
- CPC G06F9/3869
- G06F9/54
- CPC G06F9/546
- G06F30/12
- G06F30/17
- G06F30/18
- CPC G06F30/12
- G06Q10/0633
- G06Q10/04
- G06Q50/30
- CPC G06Q10/0633
- G08G5/00
- CPC G08G5/0047
- G08G5/02
- G06F3/0482
- G06F3/0484
- G06T11/00
- CPC G08G5/025
- H01J35/06
- H01J19/44
- H01J23/07
- CPC H01J35/06
- H01Q1/28
- H01Q1/08
- H01Q15/16
- CPC H01Q1/288
- H01Q7/08
- H01Q1/38
- CPC H01Q7/08
- CPC H01Q15/161
