公开(公告)号：US20240359791A1

公开(公告)日：2024-10-31

申请号：US18560301

申请日：2022-05-10

申请人： Synanarchos KALAVRIANOS

发明人： Synanarchos KALAVRIANOS

IPC分类号： B64C3/38 ,  B64C21/04 ,  B64C29/00 ,  B64C39/08 ,  B64D27/33

CPC分类号： B64C3/385 ,  B64C29/0025 ,  B64C39/08 ,  B64D27/33 ,  B64C21/04

摘要： The present invention relates to an aircraft. The aircraft comprises a fuselage, a propulsion mounting spar, a propulsion unit, and a tillable wing. The propulsion unit is mounted to the fuselage by the propulsion mounting spar. The ti liable wing is spaced apart from the propulsion mounting spar. The tillable wing is disposed in the wake from the propulsion unit. The tillable wing is arranged to tilt to vary the angle of attack of the tillable wing. In use, the propulsion unit forces air over the tillable wing such that lift is generated by the wing. The angle of attack of the wing can be increased by tilting the wing to increase the amount of lift generated by the wing. The aircraft may be configured for vertical take-off and/or landing (VTOL), or short take-off and/or landing (STOL).

公开(公告)号：US12122525B2

公开(公告)日：2024-10-22

申请号：US18296062

申请日：2023-04-05

申请人： Archer Aviation, Inc.

发明人： Jonathan Anthony Beno ,  Benjamin Scott Dyer ,  Nathan Daniel Storrs

IPC分类号： B64C29/00 ,  B60L15/06 ,  B60L15/38 ,  B64C27/54 ,  B64D27/24 ,  B64D27/30 ,  B64D33/08 ,  B64D35/02 ,  F16B2/06 ,  F16H57/08 ,  H02K1/27 ,  H02K1/32 ,  H02K5/124 ,  H02K5/20 ,  H02K7/08 ,  H02K7/116 ,  H02K9/19 ,  H02K11/33 ,  H02K15/03 ,  H02M7/5395 ,  H02P21/00 ,  H02P25/16 ,  H02P27/06 ,  H02P27/08 ,  H02K7/00

CPC分类号： B64D27/24 ,  B60L15/06 ,  B60L15/38 ,  B64C27/54 ,  B64C29/0008 ,  B64C29/0033 ,  B64D27/30 ,  B64D33/08 ,  B64D35/02 ,  F16B2/06 ,  F16H57/08 ,  H02K1/27 ,  H02K1/32 ,  H02K5/124 ,  H02K5/203 ,  H02K7/08 ,  H02K7/116 ,  H02K9/19 ,  H02K11/33 ,  H02K15/03 ,  H02M7/5395 ,  H02P21/50 ,  H02P25/16 ,  H02P27/06 ,  H02P27/08 ,  B60L2200/10 ,  B60L2210/40 ,  H02K7/006

摘要： A system for an aircraft includes a tiltable proprotor that is tiltable between a lift position for providing lift for the aircraft and a forward flight position for providing forward propulsion for the aircraft is provided. The system includes at least one actuator for adjusting a tilt angle of the tiltable proprotor; and at least one passive damper connected to the tiltable proprotor and configured to limit a rate of change of the tilt angle of the tiltable proprotor.

公开(公告)号：US20240343410A1

公开(公告)日：2024-10-17

申请号：US18299881

申请日：2023-04-13

申请人： HONEYWELL INTERNATIONAL INC.

发明人： John Bowler

IPC分类号： B64D45/04 ,  B64C29/00

CPC分类号： B64D45/04 ,  B64C29/00

摘要： A method and system for emergency landing routing and prioritization for an vertical takeoff and landing (VTOL) aircraft has been developed. First, an emergency condition onboard the VTOL aircraft is detected that requires a landing. The emergency condition onboard the aircraft is then categorized based on severity. All potential landing zones (LZs) for the VTOL aircraft are identified and categorized based on suitability for landing. The LZs for the VTOL aircraft are prioritized based on the severity of the emergency condition onboard the aircraft in view of the suitability of the LZs. Finally, a priority listing of the LZs displayed to an aircrew member of the VTOL aircraft.

公开(公告)号：US20240343388A1

公开(公告)日：2024-10-17

申请号：US18394359

申请日：2023-12-22

申请人： Goodrich Actuation Systems Limited

发明人： Antony MORGAN

IPC分类号： B64C27/605 ,  B64C27/32 ,  B64C27/52 ,  B64C27/57 ,  B64C27/64 ,  B64C29/00 ,  B64F5/60

CPC分类号： B64C27/605 ,  B64C27/322 ,  B64C27/52 ,  B64C27/57 ,  B64C27/64 ,  B64C29/0033 ,  B64F5/60 ,  B64D2221/00

摘要： A method for driving a tilt rotor between vertical and horizontal using a variable displacement motor controlled in response to a swash angle of the motor measured in a feedback loop. The loop includes an algorithm configured to monitor change in swash angle as the motor speed reduces and the actual tilt position of the rotor pylon approaches the second position and, based on the change and actual tilt position, to limit change in swash angle to be within a predetermined range as a percentage of the operating load.

公开(公告)号：US12110117B2

公开(公告)日：2024-10-08

申请号：US17408694

申请日：2021-08-23

申请人： Goodrich Corporation

发明人： Richard J. Carpino, II

IPC分类号： B64D15/12 ,  B64C27/00 ,  H05B3/18 ,  B64C29/00

CPC分类号： B64D15/12 ,  B64C27/001 ,  H05B3/18 ,  B64C2027/003 ,  B64C29/0033 ,  H05B2214/02

摘要： Pendulum dampers are described. The pendulum dampers include a damper body having a first end and a second end, with an axial direction defined between the first end and the second end with a heater bore passing through the damper body in the axial direction from a tail port at the second end toward the first end and a cartridge heater installed within the heater bore, the cartridge heater configured to generate heat and heat a material of the damper body.

公开(公告)号：US12109911B2

公开(公告)日：2024-10-08

申请号：US17751072

申请日：2022-05-23

申请人： ROLLS-ROYCE plc

发明人： Michael Adam Zagrodnik ,  Krishnamoorthi Sivalingam ,  Satyanarayana Reddy Gajjela ,  Vidor Veres-Székely ,  Daniel Lorincz ,  István Örökös-Tóth ,  Anand Prabhu Mathivanan ,  Umesh Mahajan ,  Rakesh Murali

IPC分类号： B60L58/26 ,  B64C29/00 ,  B64D33/08

CPC分类号： B60L58/26 ,  B64C29/0008 ,  B64D33/08 ,  B60L2200/10

摘要： Aircraft with battery thermal regulation systems, including: an aircraft air inlet and an aircraft air outlet; a battery pack including battery cells; and a battery thermal regulation system including a first air channel, a surface of which is in thermal communication with the battery cells so that air flowing through the first air channel exchanges heat with the cells through the surface; and an airflow device for driving an airflow. The battery thermal regulation system has a first and a second mode operation. In the first mode, the first air channel is fluidly connected with the aircraft air inlet and the aircraft air outlet whereby, during flight of the aircraft, air can enter the aircraft through the air inlet, flow through the first air channel and exit the aircraft through the air outlet. In the second mode, the airflow device drives an airflow through the first air channel.

公开(公告)号：US20240327012A1

公开(公告)日：2024-10-03

申请号：US17966251

申请日：2022-10-14

申请人： BETA AIR, LLC

发明人： Collin Freiheit ,  Cody Spiegel ,  Nicholas Moy

IPC分类号： B64D31/06 ,  B64C29/00 ,  B64D31/16

CPC分类号： B64D31/06 ,  B64D31/16 ,  B64C29/0008

摘要： A lift lever assembly for a vertical takeoff and landing (VTOL) aircraft is disclosed. The assembly includes a lever configured to control a lift propulsor of an aircraft. The assembly additionally includes at least a handle mechanically coupled to the lever, wherein the handle configured to allow transition of the lever from a thrust-engaged position to a thrust-disengaged position when the at least a handle is in an active position. The assembly also includes at least a sensor in communication with the lever, wherein the at least a sensor is configured to identify when the lever transitions from the thrust-engaged position to the thrust-disengaged position.

公开(公告)号：US20240327006A1

公开(公告)日：2024-10-03

申请号：US18619292

申请日：2024-03-28

申请人： HONDA MOTOR CO., LTD.

发明人： Kenta Uchida

IPC分类号： B64D27/357 ,  B64C29/00 ,  B64D31/16

CPC分类号： B64D27/357 ,  B64C29/0025 ,  B64D31/16

摘要： An electric power system of a flying object may supply power to electric loads including a VTOL motor and a cruise motor. A control device includes an acquisition unit, a determination unit that determines whether a power surplus situation in which surplus power obtained by deducting the required power from the sum of the generated power and the regenerated power is larger than the maximum allowable power is brought about, and a control unit that can execute power consumption increase control for increasing power consumption by reducing the operation efficiency of the cruise motor in the power surplus situation.

公开(公告)号：US20240326599A1

公开(公告)日：2024-10-03

申请号：US18737373

申请日：2024-06-07

申请人： Archer Aviation Inc.

发明人： Saienath POOPALARAJAH ,  Pedro Roberto Paterson CARLEIAL ,  Paul FRIHAUF

IPC分类号： B60L3/04 ,  B60L50/60 ,  B64C29/00 ,  H01M50/583 ,  H02H7/20

CPC分类号： B60L3/04 ,  B60L50/60 ,  H01M50/583 ,  H02H7/20 ,  B60L2200/10 ,  B64C29/0008 ,  H01M2200/103 ,  H01M2220/20

摘要： An electrical system for an aircraft, comprising at least one processor configured to: receive aircraft movement information, detect that the movement information indicates a potential crash, detect a loss of continuity in at least one low voltage wire, and blow a battery pack fuse to disconnect supply of the high voltage power to the aircraft.

公开(公告)号：US12103697B2

公开(公告)日：2024-10-01

申请号：US17647525

申请日：2022-01-10

申请人： HELENG INC.

发明人： Jack Ing Jeng

IPC分类号： B64D35/06 ,  B64C1/00 ,  B64C11/00 ,  B64C11/48 ,  B64C25/56 ,  B64C29/00 ,  B64D17/80

CPC分类号： B64D35/06 ,  B64C1/0009 ,  B64C11/001 ,  B64C11/48 ,  B64C25/56 ,  B64C29/0033 ,  B64D17/80

摘要： An aircraft includes a fuselage having a top surface opposite a bottom surface, a front section, a center section, and a rear section. A first mounting rod and a second mounting rod are coupled to the top surface. The first mounting rod and the second mounting rod are single rods. A first and a second wing are coupled to the center section. A plurality of power generator systems are coupled to the first mounting rod or the second mounting rod. Each power generator system includes a power source, a first propeller and a second propeller. The power source is configured to drive the first propeller and the second propeller. The first propeller and the second propeller have an axis of rotation, and are pivotable between a first position and a second position. A shroud encloses the power generator system.