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公开(公告)号：US11720123B2
公开(公告)日：2023-08-08
申请号：US17108704
申请日：2020-12-01
发明人： Marc Ouellet , Guillaume Biron , Alexis Dugré
CPC分类号： G05D1/0808 , B64C27/82 , G05D1/0066 , B64C2027/8209 , B64C2027/8227 , B64C2027/8254
摘要： A yaw control system for a helicopter having an airframe that includes a tailboom includes one or more tail rotors rotatably coupled to the tailboom and a flight control computer implementing an airframe protection module. The airframe protection module includes an airframe protection monitoring module configured to monitor one or more flight parameters of the helicopter and an airframe protection command module configured to modify one or more operating parameters of the one or more tail rotors based on the one or more flight parameters of the helicopter, thereby protecting the airframe of the helicopter.
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公开(公告)号：US11685524B2
公开(公告)日：2023-06-27
申请号：US17108651
申请日：2020-12-01
发明人： Marc Bustamante , Marc Ouellet , Alexis Dugré , Chen Kuang , Guillaume Biron
IPC分类号： B64C27/82
CPC分类号： B64C27/82 , B64C2027/8209 , B64C2027/8227 , B64C2027/8254
摘要： A yaw control system for a helicopter having a tailboom includes one or more tail rotors rotatably coupled to the tailboom and a quiet mode controller. The quiet mode controller includes a noise monitoring module configured to monitor one or more flight parameters of the helicopter and a quiet mode command module configured to selectively switch the one or more tail rotors to a quiet mode based on the one or more flight parameters. The quiet mode command module is also configured to modify one or more operating parameters of the one or more tail rotors in the quiet mode to reduce noise emitted by the helicopter.
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公开(公告)号：US20180111680A1
公开(公告)日：2018-04-26
申请号：US15298959
申请日：2016-10-20
CPC分类号： B64C27/025 , B64C27/18 , B64C27/82 , B64C2027/8209 , B64C2027/8236 , B64D27/02 , B64D27/24 , B64D2027/026 , B64F1/362 , Y02T50/44 , Y02T50/64
摘要： A rotorcraft capable of a hover mode and a forward cruise mode including a fuselage, a first electric propulsion system, a second electric propulsion system, and an electric power control unit to control power to the first and second electric propulsion systems in the hover and forward cruise modes. The first electric propulsion system is a tip jet cold flow system that imparts rotation on a pair of rotor blades disposed above a top surface of the fuselage, and a first electric motor configured to drive the tip jet cold flow system. The second electric propulsion system includes a propeller disposed in the rear of the fuselage and a second electric motor configured to drive the propeller.
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公开(公告)号：US09631516B2
公开(公告)日：2017-04-25
申请号：US13811875
申请日：2011-07-15
申请人： Jens Hamann , Hans-Georg Köpken , Dietmar Stoiber
发明人： Jens Hamann , Hans-Georg Köpken , Dietmar Stoiber
摘要： The invention relates to a drive (1) of a tail rotor (12) of a helicopter (10) by a permanently excited transversal flux machine in duplex arrangement in such a way that between two stators (4), which each have a toroidal winding system (8), there is arranged a disc-shaped impeller (5), which has permanent magnets (15) and on the outer circumference of which propeller blades (14) of the tail rotor (12) are arranged.
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公开(公告)号：US20140290208A1
公开(公告)日：2014-10-02
申请号：US14236621
申请日：2012-08-03
IPC分类号： F02C9/16
CPC分类号： F02C9/16 , B64C27/04 , B64C2027/8209 , B64D2027/026 , Y02T50/64
摘要： A drive system of at least one rotor of an aircraft via electrical energy in addition to or as a replacement of a mechanical system. The electrical energy is provided at least in part by at least one device for recovering thermal energy from hot gases of an internal combustion engine of the aircraft.
摘要翻译： 除了机械系统之外或作为机械系统的替代物，经由电能的飞行器的至少一个转子的驱动系统。 至少部分地由至少一个用于从飞行器的内燃机的热气体中回收热能的装置提供电能。
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公开(公告)号：US08596569B2
公开(公告)日：2013-12-03
申请号：US13200558
申请日：2011-09-26
申请人： Jason Everett Cole
发明人： Jason Everett Cole
IPC分类号： B64C27/82
CPC分类号： B64C27/04 , B64C27/467 , B64C27/82 , B64C2027/8209 , B64C2027/8236 , B64C2027/8254
摘要： My invention is a helicopter having a front electric anti-torque rotor for the purpose of having a mechanically driven pusher propeller at the rear for increasing forward speed. Speed has been a limiting factor in vertical flight. Various designs have been conceived by people around the world to make helicopters go faster. My design is a high speed single rotor helicopter design that uses a gas-electric hybrid front electric anti-torque rotor system to allow for a mechanically driven pusher propeller at the rear. As the helicopter goes forward, the front electric anti-torque gives control and the mechanically driven pusher propeller at the rear gives increased forward speed. The intent of the design is to make a high speed single rotor helicopter design.
摘要翻译： 我的发明是一种具有前电动反扭矩转子的直升机，其目的是在后部具有机械驱动的推进推进器以增加向前速度。 速度一直是垂直飞行的限制因素。 世界各地的人们已经设想出各种设计，使直升机走得更快。 我的设计是一种高速单转子直升机设计，采用气电混合式前置电动反扭矩转子系统，以便在后部采用机械驱动的推进式推进器。 随着直升机的向前，前部电动反扭矩给予控制，机械驱动的推进器在后方提供了前进的速度。 设计的目的是使高速单转子直升机设计。
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公开(公告)号：US20120305699A1
公开(公告)日：2012-12-06
申请号：US13200558
申请日：2011-09-26
申请人： Jason Everett Cole
发明人： Jason Everett Cole
CPC分类号： B64C27/04 , B64C27/467 , B64C27/82 , B64C2027/8209 , B64C2027/8236 , B64C2027/8254
摘要： My invention is a helicopter having a front electric anti-torque rotor for the purpose of having a mechanically driven pusher propeller at the rear for increase forward speed. Speed has been a limiting factor in vertical flight. Various designs have been conceived by people around the world to make the helicopter go faster. My design is a high speed single rotor helicopter design that uses a gas-electric hybrid front electric anti-torque rotor system to allow for a mechanically driven pusher propeller at the rear. As the helicopter go forward, the front electric anti-torque gives control and the mechanically driven pusher propeller at the rear gives increase forward speed. The intent of the design is to make a high speed single rotor helicopter design.
摘要翻译： 我的发明是具有前电动反扭矩转子的直升机，其目的是在后部具有机械驱动的推进推进器以增加前进速度。 速度一直是垂直飞行的限制因素。 世界各地的人们已经设想出各种设计，使直升机走得更快。 我的设计是一种高速单转子直升机设计，采用气电混合式前置电动反扭矩转子系统，以便在后部采用机械驱动的推进式推进器。 当直升机向前走时，前面的电动反扭矩给予控制，后方的机械驱动的推进器推进器提高了前进速度。 设计的目的是使高速单转子直升机设计。
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公开(公告)号：US20230415886A1
公开(公告)日：2023-12-28
申请号：US18244785
申请日：2023-09-11
发明人： Pranay Sinha , Damon Vander Lind
IPC分类号： B64C29/00 , G05D1/10 , B64C13/48 , B64C39/12 , B64D27/24 , B64D27/26 , B60L53/00 , B60L50/64 , B64C27/82 , B64D27/02 , B64D31/06
CPC分类号： B64C29/0033 , B64D2027/026 , B64C13/48 , B64C39/12 , B64D27/24 , B64D27/26 , B60L53/00 , B60L50/64 , B64C27/82 , B64D27/02 , B64D31/06 , B64D2027/264 , B60L2200/10 , B64C2027/8209 , G05D1/101
摘要： During a cruise mode, a cruise-only propeller provides thrust using power from a first power source. During a hovering mode and a transitional mode, the propeller provides no thrust. The first power source includes an internal combustion engine; a second power source includes a high discharge rate battery and a high energy battery. The propeller is electrically connected to the first power source and is electrically disconnected from the second power source. During the hovering mode and the transitional mode, a hover-and-transition-only tiltrotor provides thrust using power from the second power source. During a vertical landing, the tiltrotor switches power sources from the high energy battery to the high discharge rate battery, independent of current draw. The tiltrotor is electrically disconnected from the first power source and is electrically connected to the second power source. During the cruise mode, the tiltrotor provides no thrust.
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公开(公告)号：US20230159156A1
公开(公告)日：2023-05-25
申请号：US17818863
申请日：2022-08-10
CPC分类号： B64C13/503 , B64C27/04 , B64C27/57 , B64C2027/8209
摘要： There is disclosed in one example a flight control computer for a rotary aircraft, including: a first interface to communicatively couple to a flight control input; a second interface to communicatively couple to flight geometry actuators; a data source; a multi-dimensional lookup table including a data structure to correlate flight control inputs to flight geometry actuator outputs according to a third-factor; and circuitry and logic instructions to: receive an input via the first interface; query the data source for the third-factor; query the multi-dimensional lookup table for a control input modifier according to the flight control input and the third-factor; and compute and send via a third interface a flight geometry output according to the control input modifier.
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20.发明申请公开(公告)号：US20180346135A1
公开(公告)日：2018-12-06
申请号：US15609779
申请日：2017-05-31
CPC分类号： B64C27/12 , B64C27/82 , B64C2027/8209 , B64C2027/8227 , H02P3/04
摘要： The present invention includes a system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprising: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.
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