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1. 发明授权

US11639667B2 Rotor support device, rotor, gas turbine engine, and aircraft 有权
公开(公告)号：US11639667B2
公开(公告)日：2023-05-02
申请号：US16192718
申请日：2018-11-15
申请人： SUBARU CORPORATION
发明人： Hiroki Kato , Maki Kikuchi
IPC分类号： F01D11/10 , B64C23/00 , F01D11/20 , F15D1/00 , B64C11/00 , B64C27/82 , B64C29/00
摘要： A rotor support device includes a plurality of first electrodes, a plurality of second electrodes, a dielectric material, and at least one alternating-current power supply. The dielectric material is disposed between the plurality of first electrodes and the plurality of second electrodes. The at least one AC power supply is configured to apply an alternating-current voltage across the plurality of first electrodes and the plurality of second electrodes and induce flows of gas by causing dielectric barrier discharge between the plurality of first electrodes and the plurality of second electrodes. At least one of the plurality of first electrodes or the plurality of second electrodes is disposed apart from each other in a static system that is stationary with respect to a rotor provided in an aircraft. The static system is adjacent to the rotor.

2. 发明授权

US11630455B2 System and method for autonomous decision making, corrective action, and navigation in a dynamically changing world 有权
公开(公告)号：US11630455B2
公开(公告)日：2023-04-18
申请号：US16259463
申请日：2019-01-28
申请人： Walmart Apollo, LLC
发明人： John J. O'Brien , Donald R. High , Brian McHale , David Winkle
IPC分类号： G05D1/00 , G05D1/10 , G08G5/00 , G05D1/02 , B64C23/00 , G06N20/00
摘要： An autonomous vehicle system includes a body and a plurality of sensors coupled to the body and configured to generate a plurality of sensor measurements corresponding to the plurality of sensors. The system also includes a control unit configured to: receive inputs from a plurality of sources wherein the plurality sources comprise the plurality of sensors, the inputs comprise the plurality of sensor measurements; determine a confidence level of each input based on other inputs; prioritize, based on the confidence level associated with each input, the inputs; generate, based on the prioritization of the inputs and the confidence level, a combined input with a combined confidence level; and determine, based on the combined input and the combined confidence level, a mission task to be performed.

3. 发明授权

US11618554B2 Driving apparatus of flight object 有权
公开(公告)号：US11618554B2
公开(公告)日：2023-04-04
申请号：US17314350
申请日：2021-05-07
申请人： Banghyen Choi
发明人： Banghyen Choi
IPC分类号： B64C23/00 , H02N2/00
摘要： The present invention provides a driving apparatus of a flight object, the driving apparatus comprising: a support member rotatably installed inside a flight object body; a first rotation actuating part installed on the support member; a second rotation actuating part installed on the first rotation actuating part in a direction intersecting with the first rotation actuating part, and a magnetic body rotating vertically and horizontally by the first and the second rotation actuating part, wherein the magnetic body includes: a hemisphere rotation body installed on the second rotation actuating part; a current body installed inside the hemisphere rotation body and supplied electronic currents; a first pole magnetic body installed in one side of the current body; a second pole magnetic body installed in the other side, and a connection part connecting between the first and the second pole magnetic body.

4. 发明授权

US11618548B2 Shear hardening material to suppress flutter in inflatable wings 有权
公开(公告)号：US11618548B2
公开(公告)日：2023-04-04
申请号：US17165186
申请日：2021-02-02
申请人： Toyota Motor Engineering & Manufacturing North America, Inc.
发明人： Umesh N. Gandhi , Ryohei Tsuruta
IPC分类号： B64C3/30 , B64C23/00 , B64C37/00
摘要： A reinforced, foldable component for an aircraft is provided, configured to stabilize a high frequency aeroelastic fluttering movement. The reinforced component may include a frame structure defining at least one air chamber, and a plurality of sealed compartments. A shear thickening fluid is disposed in at least one of the sealed compartments, exhibiting a decreasing viscosity responsive to an impact force. The frame structure may define one of an inflatable wing structure, a fairing structure, an aileron structure, and a stabilizer structure, and the like. The foldable component may include an exterior layer with an exterior surface exposed to an external environment and an interior layer adjacent the at least one air chamber, wherein the plurality of sealed compartments are disposed between the exterior layer and the interior layer. The exterior layer or the interior layer may include an impact-resistant fabric layer including a shear thickening material.

5. 发明授权

US11584506B2 Aircraft wing assemblies 有权
公开(公告)号：US11584506B2
公开(公告)日：2023-02-21
申请号：US16701487
申请日：2019-12-03
申请人： BOMBARDIER INC.
发明人： Fassi Kafyeke , Francois Pepin , Farzad Mokhtarian , David Leblond
IPC分类号： B64C3/14 , B64C3/16 , B64C7/02 , B64C9/20 , B64C23/00
摘要： An aircraft and an aircraft wing assembly for an aircraft. The wing assembly includes a wing body assembly including a wing body; and at least one protruding portion connected to the wing body. The protruding portion extends aftwardly from an aft side of the wing body assembly, a leading edge of the wing body assembly defining a leading edge line, a trailing edge of the wing body assembly defining a trailing edge line extending between the inboard end and the outboard end, the trailing edge including a trailing edge of the protruding portion, the trailing edge line being a smooth line, a chord distance being defined longitudinally from the leading edge line to the trailing edge line, the chord distance at a center of the protruding portion being greater than the chord distance inboard of protruding portion and outboard of the protruding portion.

6. 发明申请

US20230027852A1 SYSTEM AND METHOD OF ROTOR MANAGEMENT 有权
公开(公告)号：US20230027852A1
公开(公告)日：2023-01-26
申请号：US17383667
申请日：2021-07-23
申请人： BETA AIR, LLC
发明人： Herman Wiegman
IPC分类号： B64C29/00 , B64C27/32 , B64C23/00
摘要： In an aspect, a system comprising a computing device. The computing device is configured to determine a drag minimization axis of a rotor connected to an aircraft. The rotor includes a first end and a second end. The rotor is configured to rotate about an axis. The computing device is further configured to determine a halting point of the rotor, wherein the halting point includes a drag minimization axis of the rotor. The computing device is configured to send a halting command to at least a magnetic element to halt the rotor, wherein the halting process is configured to stop a movement of the rotor and position the rotor in the halting point. The position of the rotor in the halting point includes the first end pointing in one direction of the drag minimization axis and the second end pointing in an opposite direction of the first end.

7. 发明申请

US20220349391A1 VARIABLE-POROSITY PANEL SYSTEMS AND ASSOCIATED METHODS 有权
公开(公告)号：US20220349391A1
公开(公告)日：2022-11-03
申请号：US17679696
申请日：2022-02-24
申请人： The Boeing Company
发明人： Frederick T. Calkins , Douglas E. Nicholson , Jordan Kreitzman
IPC分类号： F03G7/06 , B64C23/00 , F03G7/00
摘要： Variable-porosity panel systems and associated methods. A variable-porosity panel system includes a panel assembly with an exterior layer defining a plurality of exterior layer pores and a sliding layer adjacent to the exterior layer and defining a plurality of sliding layer pores. The variable-porosity panel system additionally includes a shape memory alloy (SMA) actuator configured to translate the sliding layer relative to the exterior layer to modulate a porosity of the panel assembly. The SMA actuator includes an SMA element configured to exert an actuation force on the sliding layer and at least partially received within an SMA element receiver of the sliding layer. The SMA element extends out of the sliding layer only at a sliding layer first end. A method of operating the variable-porosity panel system includes assembling the variable-porosity panel system and/or transitioning the panel assembly of the variable-porosity panel system among the plurality of panel configurations.

8. 发明授权

US11459092B2 Aircraft steering system, aircraft, and aircraft steering method 有权
公开(公告)号：US11459092B2
公开(公告)日：2022-10-04
申请号：US16375141
申请日：2019-04-04
申请人： SUBARU CORPORATION
发明人： Hiroki Kato , Nobuyuki Nakazato , Iwao Murata
IPC分类号： B64C13/50 , B64C23/00 , F16D37/00
摘要： An aircraft steering system includes an electric actuator, a clutch, at least one plasma actuator, and a controller. The electric actuator is configured to vary an angle of a flight control surface of an aircraft. The clutch is configured to cut off torque by driving of the electric actuator. The torque is to be transmitted to the flight control surface. The at least one plasma actuator is configured to form a flow of air on a surface of the flight control surface when the torque is cut off. The controller is configured to control the electric actuator, the clutch, and the at least one plasma actuator.

9. 发明授权

US11312471B2 Aircraft drag reduction system and internally cooled motor system and aircraft using same 有权
公开(公告)号：US11312471B2
公开(公告)日：2022-04-26
申请号：US16355745
申请日：2019-03-16
申请人： Joby Aero, Inc.
发明人： JoeBen Bevirt , Gregor Veble Mikic , Joey Milia , Rob Thodal , Vishnu Vithala
IPC分类号： B64C1/38 , B64C23/00 , B64C21/08 , B64C27/32
摘要： An aircraft propulsion system with a drag reduction portion adapted to reduce skin friction on at least a portion of the external surface of an aircraft. The drag reduction portion may include an inlet to ingest airflow. The aircraft may also have an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

10. 发明授权

US11111028B2 Variable and adaptable diverterless bump inlet 有权
公开(公告)号：US11111028B2
公开(公告)日：2021-09-07
申请号：US15992861
申请日：2018-05-30
申请人： Airbus Defence and Space GmbH
发明人： Thomas Berens
IPC分类号： B64D33/02 , F02C7/042 , F02C7/057 , B64C23/00
摘要： A device for a variable and adaptable diverterless bump engine inlet of an aircraft comprises a flexible inlet, a mechanism to change the shape of the flexible inlet, and a processing unit to control the mechanism. The flexible inlet of the device includes a plurality of edges attached partly to a fuselage skin and partly to an engine inlet duct. With this device, the shape of the flexible inlet can be controlled according to the flight conditions, and hence the engine air intake will perform more efficient at all speeds while fulfilling requirements for less radar visibility.

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