公开(公告)号：US20240246685A1

公开(公告)日：2024-07-25

申请号：US18330776

申请日：2023-06-07

申请人： Archer Aviation, Inc.

发明人： Scott GRAVES ,  Alan D. TEPE ,  Robert Wayne MOORE

IPC分类号： B64D27/24 ,  B64C27/54 ,  B64C29/00 ,  B64D33/08 ,  B64D35/02 ,  F16H57/08 ,  H02K1/27 ,  H02K1/32 ,  H02K5/20 ,  H02K7/08 ,  H02K7/116 ,  H02K9/19 ,  H02K11/33 ,  H02K15/03 ,  H02K7/00

CPC分类号： B64D27/24 ,  B64C27/54 ,  B64C29/0008 ,  B64C29/0033 ,  B64D33/08 ,  B64D35/02 ,  F16H57/08 ,  H02K1/27 ,  H02K1/32 ,  H02K5/203 ,  H02K7/08 ,  H02K7/116 ,  H02K9/19 ,  H02K11/33 ,  H02K15/03 ,  H02K7/006

摘要： An electric propulsion system for a vertical takeoff-and-landing aircraft having an inverter assembly, a gearbox assembly, an electric motor assembly. The inverter assembly, the gearbox assembly, and the electric motor assembly may be substantially aligned along an axis. The inverter assembly, a gearbox assembly, and electric motor assembly may each abut at least one of the others. The electric engine may use a liquid, such as oil, for cooling and lubricating components of the inverter assembly, gearbox assembly, and electric motor assembly. Further, the electric engine may use volumes of oil for cooling and lubricating components below a threshold volume so that the electric engines do not require a fire protective barrier.

公开(公告)号：US12043376B2

公开(公告)日：2024-07-23

申请号：US16647817

申请日：2018-09-06

申请人： AMSL Innovations Pty Ltd

发明人： Andrew Dudley Moore

IPC分类号： B64C29/00 ,  B60L15/20 ,  B64C3/38 ,  B64C9/00 ,  B64C9/16 ,  B64C13/00 ,  B64C27/52 ,  B64C27/80 ,  B64C27/82 ,  B64C39/06 ,  B64D27/24

CPC分类号： B64C29/0033 ,  B60L15/20 ,  B64C3/38 ,  B64C9/00 ,  B64C9/16 ,  B64C13/00 ,  B64C27/52 ,  B64C27/80 ,  B64C27/82 ,  B64C39/068 ,  B64D27/24 ,  B60L2200/10 ,  B64C2027/8227

摘要： A vertical take-off and landing (VTOL) aircraft (10) comprises a fuselage (24) first and second forward wings (20, 22) and first and second rearward wings (30, 32), each wing having a fixed leading edge (25, 35) and a trailing control surface (50) which is pivotal about a generally horizontal axis. Electric rotors (60) are mounted to the wings (20, 22, 30, 32), the electric rotors (60) being pivotal with the trailing control surface (50) between a first position in which each rotor (60) has a generally vertical axis of rotation, and a second position in which each rotor (60) has a generally horizontal axis of rotation; wherein at least one of the wings (20, 22, 30, 32) has a first and a second electric rotor (60) which are each mounted having non-parallel axes of rotation so that the thrust lines of the first and second electric rotors are different.

公开(公告)号：US12037133B2

公开(公告)日：2024-07-16

申请号：US18071862

申请日：2022-11-30

申请人： AIRBUS SAS

发明人： Thomas Fulcher

IPC分类号： B64D45/02 ,  B64D27/24 ,  B64D27/40 ,  H01B9/02 ,  H02K7/18

CPC分类号： B64D45/02 ,  B64D27/24 ,  B64D27/40 ,  H01B9/02 ,  H02K7/1807 ,  B64D2221/00

摘要： An aircraft is disclosed include wiring configured to carry electrical power; and an electromagnetic shielding arrangement which provides an enclosure around the wiring and is configured to block electromagnetic emissions from the wiring. The electromagnetic shielding arrangement includes a first shield; a second shield which can move relative to the first shield; and a gap between overlapping portions of the shields. The gap is configured to enable air to flow into or out of the enclosure via the gap.

公开(公告)号：US12037126B1

公开(公告)日：2024-07-16

申请号：US16568904

申请日：2019-09-12

申请人： SmartGridz, Inc.

发明人： Marija Ilic ,  Rupamathi Jaddivada

IPC分类号： B64D31/06 ,  B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C9/48 ,  G06F30/13 ,  G06F30/15 ,  G06F30/17 ,  G06F30/20 ,  G06F119/02 ,  G06F119/06 ,  G06F119/14 ,  G06F119/16

CPC分类号： B64D31/06 ,  B64D27/02 ,  B64D27/10 ,  B64D27/24 ,  F02C9/48 ,  B64D2027/026 ,  B64D2221/00 ,  G06F30/13 ,  G06F30/15 ,  G06F30/17 ,  G06F30/20 ,  G06F2119/02 ,  G06F2119/06 ,  G06F2119/14 ,  G06F2119/16

摘要： Disclosed herein is a fundamental modeling and control method in dynamic energy conversion and transfers in complex energy systems with multiple energy sources, fuel and electric. The multi-layered modeling enables efficient and stable operation through optimized coordination of engines and electric part of a hybrid turbo-electric distribution system (TeDP). A provable coordination of power and rate of change of power interactions between the components is done at the higher-system level. Advanced nonlinear control of components is disclosed to ensure that components meet power/rate of change of power commands given by the higher level. This method is used to demonstrate, for the first time, how rotor stall and surge instabilities in engines can be eliminated by controlling the electric generators and/or storage.

公开(公告)号：US12037124B2

公开(公告)日：2024-07-16

申请号：US17581098

申请日：2022-01-21

申请人： General Electric Company

发明人： Honggang Wang ,  Michael Anthony Benjamin ,  Seung-Hyuck Hong ,  Richard L. Hart

IPC分类号： B64D27/24 ,  B64D27/10 ,  F02C7/26 ,  H01M8/04111 ,  H01M8/04223 ,  H01M8/04225 ,  H01M8/04701 ,  B64D27/02 ,  B64D41/00 ,  F02C1/10

CPC分类号： B64D27/24 ,  B64D27/10 ,  F02C7/26 ,  H01M8/04111 ,  H01M8/04225 ,  H01M8/04231 ,  H01M8/04708 ,  H01M8/04738 ,  B64D27/026 ,  B64D2041/005 ,  F02C1/10 ,  H01M2250/20

摘要： A method for operating a propulsion system for an aircraft, the propulsion system including a gas turbine engine and a fuel cell assembly, the fuel cell assembly comprising a fuel cell stack having a fuel cell defining an outlet positioned to remove output products from the fuel cell during operation, the method including: executing a startup sequence for the gas turbine engine, wherein executing the startup sequence comprises initiating the startup sequence for the gas turbine engine; executing a startup sequence for the fuel cell assembly concurrently with, or subsequent to, initiating the startup sequence for the gas turbine engine; and operating the fuel cell assembly to provide output products to a combustion section of the gas turbine engine.

公开(公告)号：US12030656B1

公开(公告)日：2024-07-09

申请号：US18599703

申请日：2024-03-08

申请人： Archer Aviation Inc.

发明人： Scott Graves ,  Alan D. Tepe ,  Robert Wayne Moore

IPC分类号： B64D33/08 ,  B64C29/00 ,  B64D27/24 ,  B64D27/30

CPC分类号： B64D27/24 ,  B64C29/0033 ,  B64D27/30 ,  B64D33/08

摘要： An electric propulsion system for a vertical take-off and landing (VTOL) aircraft having a heat exchanger to cool fluids used in an electrical engine, the electric propulsion system comprising at least one electrical engine mechanically connected directly or indirectly to a fuselage of the VTOL aircraft and electrically connected to an electrical power source. The electrical engine may comprise an electrical motor having a stator and a rotor; a gearbox assembly comprising a sun gear; at least one planetary gear; a ring gear; and a planetary carrier. The electric engine may include an inverter assembly comprising a thermal plate and an inverter assembly housing; an end bell assembly that is connected to the thermal plate of the inverter assembly; and a heat exchanger comprising an array of cooling fins and tubes.

公开(公告)号：US12030655B2

公开(公告)日：2024-07-09

申请号：US17751172

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-Szekely ,  Daniel Lorincz ,  István Örökös-Tóth ,  Anand Prabhu Mathivanan

IPC分类号： H01M10/613 ,  B60L50/64 ,  B60L58/26 ,  B64C29/00 ,  B64D27/24

CPC分类号： B64D27/24 ,  B60L50/64 ,  B60L58/26 ,  B64C29/0033 ,  H01M10/613 ,  B60L2200/10 ,  H01M2220/20

摘要： An aircraft including a battery pack having a plurality of battery cells arranged to vent into a venting region of the battery pack. A path is defined between the venting region and an exterior of the aircraft, whereby thermal products vented by the cells can exit the aircraft via the path. In some embodiments, the venting region is or is in fluid communication with an air channel through which air flows from an aircraft air inlet to an aircraft air outlet. In other embodiments, the path joins the venting region and an opening in an external surface of the aircraft.

公开(公告)号：US12030631B2

公开(公告)日：2024-07-09

申请号：US17732938

申请日：2022-04-29

申请人： Sandor Mark Langer

发明人： Sandor Mark Langer

IPC分类号： B64C9/02 ,  B60L50/60 ,  B64C1/14 ,  B64C25/36 ,  B64C25/52 ,  B64C29/00 ,  B64C37/02 ,  B64C39/02 ,  B64D9/00 ,  B64D27/24 ,  B64D27/40 ,  B64U30/20 ,  B64U50/19 ,  B64U101/60

CPC分类号： B64C39/024 ,  B60L50/66 ,  B64C1/1415 ,  B64C9/02 ,  B64C25/36 ,  B64C25/52 ,  B64C37/02 ,  B64D9/003 ,  B64D27/24 ,  B64D27/40 ,  B60L2200/10 ,  B64C29/0008 ,  B64U30/20 ,  B64U50/19 ,  B64U2101/60

摘要： An unmanned aerial vehicle (UAV) has a wing assembly that is coupled to a cargo carrying pod. The pod has a pallet storage volume and an aerodynamic outer surface. The wing assembly has wings that are coupled to rotor booms that include motors and rotors. A tail assembly is coupled to tail booms that extend back from the wings. Rudders are coupled to the rear portions of the tail booms and an elevator is coupled to top portions of the rudders. The elevator is at least 84 inches high and the rudders are at least 48 apart so that a forklift can drive under the elevator and between the rudders to a rear door of the pod to place cargo on a pallet into the storage area of the pod.

公开(公告)号：US20240217670A1

公开(公告)日：2024-07-04

申请号：US18223210

申请日：2023-07-18

申请人： BETA AIR, LLC

发明人： Kyle B. Clark ,  Herman Wiegman

IPC分类号： B64D37/04 ,  B64C29/00 ,  B64D27/02 ,  B64D27/24 ,  B64D35/04

CPC分类号： B64D37/04 ,  B64D27/24 ,  B64D35/04 ,  B64C29/0008 ,  B64D27/026

摘要： A fuel pod for a hybrid electric aircraft. The fuel pod includes a housing, a fuel tank, a generator and a connection mechanism. The fuel tank is contained within the housing and is configured to hold a fuel therein. The generator is contained within the housing and is connected to the fuel tank. The generator is configured to power at least one of a plurality of flight components of a hybrid electric aircraft. The connection mechanism is at the housing and is configured to removably attach the fuel pod to the hybrid electric aircraft. The connection mechanism includes an electrical interface configured to electrically link to at least one of the plurality of flight components of the hybrid electric aircraft, and a communication interface configured to communicatively link to a flight controller communicatively connected to the hybrid electric aircraft.

公开(公告)号：US12028009B2

公开(公告)日：2024-07-02

申请号：US17372349

申请日：2021-07-09

申请人： The Boeing Company

发明人： Frederic Lacaux ,  Eugene V. Solodovnik ,  Vyacheslav Khozikov

IPC分类号： H02P1/00 ,  B60L15/20 ,  B60L50/60 ,  B64C11/30 ,  B64D27/24 ,  B64D31/00 ,  H02P27/06 ,  H02P29/028

CPC分类号： H02P29/028 ,  B60L15/20 ,  B60L50/60 ,  B64C11/303 ,  B64D27/24 ,  B64D31/00 ,  H02P27/06 ,  B60L2200/10

摘要： A method for protecting an electric propulsion system in response to occurrence of a fault. The method includes the step of activating short circuits in power switches of inverters in a motor controller to redirect current regenerated by a motor which is electrically coupled to the motor controller and mechanically coupled to a propeller. The method further includes feathering the propeller while the motor is regenerating current. The protection logic is designed to address different types of faults, including faults in the high-voltage direct-current bus, faults in the motor controller, and faults in the motor.