THE BOEING COMPANY patent applications on October 17th, 2024
Patent Applications by THE BOEING COMPANY on October 17th, 2024
THE BOEING COMPANY: 20 patent applications
THE BOEING COMPANY has applied for patents in the areas of B64F5/10 (2), B64D43/00 (2), A62B7/14 (2), A62B25/00 (2), B64D11/00 (2) A01N47/44 (1), B64F5/10 (1), G08G5/003 (1), G01N21/55 (1), G01N3/36 (1)
With keywords such as: configured, fluid, aircraft, structure, flow, stamping, repair, components, within, and mask in patent application abstracts.
Patent Applications by THE BOEING COMPANY
20240341310. ANTIPATHOGENIC NANOSTRUCTURES_simplified_abstract_(the boeing company)
Inventor(s): Michael J. MONTEIRO of Brisbane (AU) for the boeing company, Valentin A. BOBRIN of Brisbane (AU) for the boeing company
IPC Code(s): A01N47/44, A01N25/34, A01P1/00, A61L2/232, A61L101/32, A61L101/40, A61L101/44, A61L101/50, A62B18/08, B82Y5/00
CPC Code(s): A01N47/44
Abstract: methods include disposing a layer of a solution or emulsion having a nanostructure on a surface. the surface further includes a sars-cov-2 virus disposed thereon. the nanostructure includes a compound or salt thereof. the compound includes one or more styrene units, one or more n-alkylacrylamide units, and a moiety represented by the formula:
20240341310. ANTIPATHOGENIC NANOSTRUCTURES_simplified_abstract_(the boeing company)
Inventor(s): Michael J. MONTEIRO of Brisbane (AU) for the boeing company, Valentin A. BOBRIN of Brisbane (AU) for the boeing company
IPC Code(s): A01N47/44, A01N25/34, A01P1/00, A61L2/232, A61L101/32, A61L101/40, A61L101/44, A61L101/50, A62B18/08, B82Y5/00
CPC Code(s): A01N47/44
Abstract:
20240341310. ANTIPATHOGENIC NANOSTRUCTURES_simplified_abstract_(the boeing company)
Inventor(s): Michael J. MONTEIRO of Brisbane (AU) for the boeing company, Valentin A. BOBRIN of Brisbane (AU) for the boeing company
IPC Code(s): A01N47/44, A01N25/34, A01P1/00, A61L2/232, A61L101/32, A61L101/40, A61L101/44, A61L101/50, A62B18/08, B82Y5/00
CPC Code(s): A01N47/44
Abstract: where ris alkyl. the compound includes a moiety represented by the formula:
20240341310. ANTIPATHOGENIC NANOSTRUCTURES_simplified_abstract_(the boeing company)
Inventor(s): Michael J. MONTEIRO of Brisbane (AU) for the boeing company, Valentin A. BOBRIN of Brisbane (AU) for the boeing company
IPC Code(s): A01N47/44, A01N25/34, A01P1/00, A61L2/232, A61L101/32, A61L101/40, A61L101/44, A61L101/50, A62B18/08, B82Y5/00
CPC Code(s): A01N47/44
Abstract:
20240341310. ANTIPATHOGENIC NANOSTRUCTURES_simplified_abstract_(the boeing company)
Inventor(s): Michael J. MONTEIRO of Brisbane (AU) for the boeing company, Valentin A. BOBRIN of Brisbane (AU) for the boeing company
IPC Code(s): A01N47/44, A01N25/34, A01P1/00, A61L2/232, A61L101/32, A61L101/40, A61L101/44, A61L101/50, A62B18/08, B82Y5/00
CPC Code(s): A01N47/44
Abstract: where ris alkyl and rand rare independently hydrogen or alkyl. the compound includes a plurality of n,n-(dialkylamino)(divalent alkyl) alkylacrylate units. one or more of the n,n-(dialkylamino)(divalent alkyl)alkylacrylate units has an unsubstituted nitrogen. one or more of the n,n-(dialkylamino)(divalent alkyl)alkylacrylate units is substituted with a c-calkyl moiety, and one or more of the n,n-(dialkylamino)(divalent alkyl) alkylacrylate units is substituted with a moiety selected from the group consisting of guanidine, polygalactose, coumarin, and combination(s) thereof.
Inventor(s): Andrew Leo Fabry of Seattle WA (US) for the boeing company, Adam Patrick Boroughs of Seattle WA (US) for the boeing company, Katia Marguerite Benson of Everett WA (US) for the boeing company, Douglas Alan Brown of Edmonds WA (US) for the boeing company, Franco Marino Cagnina of Lynnwood WA (US) for the boeing company
IPC Code(s): A62B7/14, A62B25/00, B64D11/00
CPC Code(s): A62B7/14
Abstract: an emergency oxygen system for an internal cabin of a vehicle includes a housing including one or more compartments, and one or more oxygen assemblies. the one or more oxygen assemblies include a mask and a fluid conduit. the mask is configured to be stowed within and deployed from the one or more compartments. a door is moveably secured to the housing. the door is moveable between a closed position underneath the one or more compartments to secure the mask within the one or more compartments, and an open position during a deployment event in which the mask drops down and laterally out of the one or more compartments. the mask is configured to hang down from a portion of the door when the door is in the open position. the emergency oxygen assemblies can be separate and distinct from passenger service units (psus).
Inventor(s): Dalton W. Hamburg of Bothell WA (US) for the boeing company
IPC Code(s): B22F10/322, B22F12/70, B22F12/90, B33Y30/00, B33Y50/02
CPC Code(s): B22F10/322
Abstract: methods of precisely regulating a process gas flow through a process chamber of an additive manufacturing system and related systems. the methods include positioning a removeable flow rate sensor to measure an actual bulk flow rate of the process gas flow and controlling the process gas flow to a desired bulk flow rate. the methods also include measuring the actual bulk flow rate with the removeable flow rate sensor, separating the removeable flow rate sensor from the process chamber, and comparing the actual bulk flow rate to the desired bulk flow rate. the methods further include proceeding with the additive manufacturing process or performing a corrective action and subsequently proceeding with the additive manufacturing process.
20240342842. COMPOSITE STRUCTURE REPAIR SYSTEM_simplified_abstract_(the boeing company)
Inventor(s): Larry D. RIDGEWAY of Snohomish WA (US) for the boeing company, Pradeep KRISHNASWAMY of Redmond WA (US) for the boeing company, Gary D. OAKES of Renton WA (US) for the boeing company, Remmelt A. STAAL of Irvine CA (US) for the boeing company
IPC Code(s): B23P6/04, B64F5/40
CPC Code(s): B23P6/04
Abstract: the present disclosure provides repair systems, repair components, and methods for repairing composite structure systems. the repair systems include using a set number of prefabricated repair components which are fabricated to repair multiple composite members in a composite structure system.
Inventor(s): Evan M. King of St. Louis MO (US) for the boeing company, Ike C. Schevers of St. Louis MO (US) for the boeing company, David L. Fritsche of St. Louis MO (US) for the boeing company
IPC Code(s): B25B31/00, B64F5/10
CPC Code(s): B25B31/005
Abstract: an example system includes: an apparatus comprising: a temporary fastener having a stem configured to be inserted through as assembly and be retained to the assembly, and a spring mounted about the stem. the system also includes a linear actuator configured to apply a force on the spring, thereby causing the spring to be compressed against the assembly and apply a predetermined clamping force to the assembly.
Inventor(s): Gregory J. Hickman of Charleston SC (US) for the boeing company, Michael P. Matlack of St. Charles MO (US) for the boeing company, Emma L. Morrissey of St. Louis MO (US) for the boeing company, Evan Lloyd of Maryville IL (US) for the boeing company, Andrew Gutknecht of St. Louis MO (US) for the boeing company
IPC Code(s): B29C51/08, B29C51/00, B29C51/10, B29C70/00
CPC Code(s): B29C51/085
Abstract: a compliant stamping tool for stamp forming a workpiece includes a support structure, a fluid and a deformable membrane. the support structure includes a support wall spaced from a stamping axis. the support wall defines a chamber with an opening. the fluid is disposed within the chamber. the deformable membrane is secured to the support wall, covers the opening and seals the fluid within the chamber. the deformable membrane defines a compliant stamping surface configured to oppose different non-compliant stamping surfaces of opposing stamping tools. a system for stamp forming a workpiece includes a first stamping tool and the compliant stamping tool. the first stamping tool defines a first non-compliant stamping surface extending from the stamping axis. a method for stamp forming a workpiece is also provided.
Inventor(s): Richard A. Prause of Arlington VA (US) for the boeing company, Andrew E. Modin of Andrew VA (US) for the boeing company, Allen Halbritter of Arlington VA (US) for the boeing company, Richard E. Heath of Arlington VA (US) for the boeing company, Ivan G. Ramirez of Arlington VA (US) for the boeing company, John R. Nibe of Arlington VA (US) for the boeing company
IPC Code(s): B29C70/50, B29L31/00
CPC Code(s): B29C70/504
Abstract: an example method of forming a composite structure includes applying a laminated charge onto an expandable pallet, moving the expandable pallet in a linear motion relative to a plurality of rollers, and progressively urging the laminated charge into a continuously expanding recess defined by the expandable pallet using the plurality of rollers. the plurality of rollers are oriented in a serial configuration so as to shape the laminated charge into at least part of a shape of the composite structure.
Inventor(s): Abigail McGuckin of Media PA (US) for the boeing company, Michael Joseph Mikuszewski of Wilmington DE (US) for the boeing company
IPC Code(s): B29C70/68, B29C70/70
CPC Code(s): B29C70/683
Abstract: elastomer intensifiers for part manufacture and methods of making elastomeric intensifiers are described herein. an example method of fabricating an intensifier includes: add a mixture to a region of a mold, the mixture including a first amount of an elastomer and a constituent; curing the mixture to form an insert having a shape corresponding to the region of the mold; adding a second amount of the elastomer to the mold and over the insert; and curing the insert and the second amount of the elastomer to form the intensifier.
Inventor(s): Umesh Hosamani of Bangalore (IN) for the boeing company, Prasad Rao Piradi of Bengaluru (IN) for the boeing company, Akshay Arun Sankeshwari of Bengaluru (IN) for the boeing company
IPC Code(s): B60T8/171, B60T8/17, B60T8/32, B64C25/42
CPC Code(s): B60T8/171
Abstract: disclosed is a controller for controlling brake action of an aircraft based on a current runway condition of the runway. the controller receives an expected condition of the runway and expected brake action for the aircraft from air traffic control, or other entity. the controller sends actual measured brake pressure applied by the aircraft while landing, along with sensor data from sensors on the aircraft configured to detect contaminants such as fluid or ice on the runway to a machine learning model. the machine learning model is configured to output a predicted brake action for the aircraft and predicted runway condition. the controller compares the expected brake action and expected runway condition to the predicted brake action and predicted runway condition. if there is any discrepancy, the controller sends the predicted brake action and runway condition to air traffic control to update the expected brake action and expected runway condition.
20240343383. Slat Movement System for Aircraft_simplified_abstract_(the boeing company)
Inventor(s): Emily Georgia Rayner of Newport (AU) for the boeing company, Kevin Raylin Tsai of Redmond WA (US) for the boeing company, Ramón Augustin Burin of Lake Stevens WA (US) for the boeing company, Bret Alan Bowers of Langley WA (US) for the boeing company
IPC Code(s): B64C9/24, B64C9/02, B64C9/06, B64C13/38
CPC Code(s): B64C9/24
Abstract: the illustrative examples provide a slat movement system for use in an aircraft. an aircraft comprises a wing having a fixed edge and a wing front spar, and a moveable slat connected to the wing by a four bar linkage and a slat arm, the slat arm movable along a track comprising a slot terminating prior to the wing front spar.
Inventor(s): Andrew Leo Fabry of Seattle WA (US) for the boeing company, Franco Marino Cagnina of Lynnwood WA (US) for the boeing company, Katia Marguerite Benson of Everett WA (US) for the boeing company, Douglas Alan Brown of Edmonds WA (US) for the boeing company
IPC Code(s): B64D11/00, A62B7/14, A62B25/00
CPC Code(s): B64D11/00
Abstract: an emergency oxygen system for an internal cabin of a vehicle includes a housing including one or more compartments. one or more oxygen assemblies include a mask and a fluid conduit. the mask is configured to be stowed within and deployed from the one or more compartments. a door is moveably secured to the housing. the door is configured to pivot in an outboard direction from a closed position to an open position during a deployment event. one or more pouches can be secured to an interior surface of the door. coiled tubing of the fluid conduit is retained by the one or more pouches when the mask is stowed within the one or more compartments. an alert device can be operatively coupled to the one or more oxygen assemblies. the alert device is configured to emit a response indicating that oxygen is flowing to the mask.
Inventor(s): Thomas Karl Tsotsis of Santa Ana CA (US) for the boeing company
IPC Code(s): B64F5/10, B33Y10/00, B33Y80/00
CPC Code(s): B64F5/10
Abstract: present systems and apparatuses and their methods of manufacture are directed to acoustic core that can be made from metal alloys or thermoplastic materials and formed into single-piece, net-shaped core details possessing one or more of the following features: varying cell size, varying cell-wall thickness, varying cell shape, varying core thickness, incorporation of wall perforations, incorporation of septums, edge closeouts, and non-vertical and/or curved cell walls.
Inventor(s): Remmelt A. STAAL of Irvine CA (US) for the boeing company, Arne K. LEWIS of Auburn WA (US) for the boeing company, Justin H. REGISTER of Charleston SC (US) for the boeing company
IPC Code(s): B64F5/40, B29C73/10, B29C73/30
CPC Code(s): B64F5/40
Abstract: the present disclosure provides repair systems, repair components, and methods for repairing composite structure systems using a set number of prefabricated repair components including a repair component and various shims which are fabricated to repair multiple composite members in a composite structure system.
Inventor(s): Steven J. Adam of Orange CA (US) for the boeing company, Erin Bangert Voltz of Madison AL (US) for the boeing company
IPC Code(s): B64G1/50
CPC Code(s): B64G1/50
Abstract: the present disclosure provides examples of thermal control systems for reducing ice formation. in one example, a space vehicle comprising a first component, a second component, and a thermal control system is provided. the thermal control system is configured for transferring thermal energy between the first component and the second component. the thermal control system comprises a fluid loop in thermal communication with the first component and the second component, a heat transfer fluid including a perfluoropolyether, an anti-icing fluid, wherein the anti-icing fluid is immiscible with the heat transfer fluid and is miscible with water to form a mixture that remains liquid at temperatures under use conditions in space, and a pump for circulating the heat transfer fluid and the anti-icing fluid within the fluid loop.
Inventor(s): Jonathan C. Morrow of Everett WA (US) for the boeing company
IPC Code(s): G01C5/00, B64D43/00
CPC Code(s): G01C5/005
Abstract: a device includes circuitry configured to, during a first operation mode, generate a static pressure indication independently of a static pressure measurement limit. the circuitry is also configured to, during a second operation mode, generate the static pressure indication based on the static pressure measurement limit. the circuitry is further configured to generate a standby altitude indication based on the static pressure indication.
Inventor(s): Bradley Jerome Rafferty of Saint Louis MO (US) for the boeing company, Paul Conrad Crnic of Saint Louis MO (US) for the boeing company
IPC Code(s): G01M9/08, G06F30/15
CPC Code(s): G01M9/08
Abstract: a method and an electronic system for modeling an aircraft in a testing tunnel includes a scale model of the aircraft in which a plurality of components is installed in the testing tunnel to form a first model configuration. each of the components includes an identifier having unique identification information for the respective components. each of the components is identifiable by the identifier when installed in the testing tunnel for the first model configuration. a host machine is configured to select data about the components installed for the first model configuration. the host machine is configured to execute instructions from a memory, via a processor. the host machine is configured to receive the unique identification information from the components of the first model configuration, determine if the unique identification information corresponds to the selected data, and output a notification if the selected data does not match the unique identification information.
Inventor(s): Morteza SAFAI of Newcastle WA (US) for the boeing company
IPC Code(s): G01N3/36
CPC Code(s): G01N3/36
Abstract: a system and method for evaluating a bond is provided. the system uses an adjustable submerged plasma probe to generate a compression wave in a first vessel containing a liquid. the system further includes a second vessel in which a vacuum is pulled to hold the first vessel against a bonded structure being inspected. the compression wave is directed to propagate from the liquid into the bonded structure to apply a known force to the bond being inspected. the adjustable submerged plasma probe allows the intensity of the compression wave to be increased or decreased at the bonded structure.
20240344980. Microspot Reflectometer_simplified_abstract_(the boeing company)
Inventor(s): Brian Gunther of St. Louis MO (US) for the boeing company, James Thaddeus Wegner of St. Louis MO (US) for the boeing company, Jeffery Thomas Murphy of Troy MO (US) for the boeing company
IPC Code(s): G01N21/55, G02B26/08
CPC Code(s): G01N21/55
Abstract: a reflectometer configured to test a sample. the reflectometer includes a light source that emits a light beam to the sample that is placed on a sample holder. the reflectometer focuses the light beam to a reduced spot size on the sample. the reflectometer is configured to view structure/defects in the sample using a detector that is downstream from the sample.
Inventor(s): Chaitanya Pavan Kumar Aripirala of Bangalore (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): G08G5/00, B64D43/00, G01C21/20
CPC Code(s): G08G5/003
Abstract: a system and a method include a control unit configured to receive a vectoring path for an aircraft. the vectoring path diverts from an air traffic service route for the aircraft. the control unit is further configured to automatically determine segments of the vectoring path, automatically monitor a position of the aircraft within an airspace, and automatically send vectoring instructions to the aircraft in response to the aircraft reaching locations within the airspace associated with one or more points of the segments.
20240347925. CONFOCAL ANTENNA SYSTEM_simplified_abstract_(the boeing company)
Inventor(s): Paul C. Werntz of Long Beach CA (US) for the boeing company, Raenaurd D. Turpin of La Mirada CA (US) for the boeing company
IPC Code(s): H01Q19/19, H01Q15/14, H01Q15/16
CPC Code(s): H01Q19/192
Abstract: a reflector for an antenna includes a first shaped region, wherein a curvature of the first shaped region is defined by a corresponding scan angle, and a second shaped region, wherein a curvature of the second shaped region is based on a corresponding scan angle. the curvature of the first shaped region is different than the curvature of the second shaped region.
THE BOEING COMPANY patent applications on October 17th, 2024
- THE BOEING COMPANY
- A01N47/44
- A01N25/34
- A01P1/00
- A61L2/232
- A61L101/32
- A61L101/40
- A61L101/44
- A61L101/50
- A62B18/08
- B82Y5/00
- CPC A01N47/44
- The boeing company
- A62B7/14
- A62B25/00
- B64D11/00
- CPC A62B7/14
- B22F10/322
- B22F12/70
- B22F12/90
- B33Y30/00
- B33Y50/02
- CPC B22F10/322
- B23P6/04
- B64F5/40
- CPC B23P6/04
- B25B31/00
- B64F5/10
- CPC B25B31/005
- B29C51/08
- B29C51/00
- B29C51/10
- B29C70/00
- CPC B29C51/085
- B29C70/50
- B29L31/00
- CPC B29C70/504
- B29C70/68
- B29C70/70
- CPC B29C70/683
- B60T8/171
- B60T8/17
- B60T8/32
- B64C25/42
- CPC B60T8/171
- B64C9/24
- B64C9/02
- B64C9/06
- B64C13/38
- CPC B64C9/24
- CPC B64D11/00
- B33Y10/00
- B33Y80/00
- CPC B64F5/10
- B29C73/10
- B29C73/30
- CPC B64F5/40
- B64G1/50
- CPC B64G1/50
- G01C5/00
- B64D43/00
- CPC G01C5/005
- G01M9/08
- G06F30/15
- CPC G01M9/08
- G01N3/36
- CPC G01N3/36
- G01N21/55
- G02B26/08
- CPC G01N21/55
- G08G5/00
- G01C21/20
- CPC G08G5/003
- H01Q19/19
- H01Q15/14
- H01Q15/16
- CPC H01Q19/192
