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81. 发明申请

US20200231297A1 Aircraft having Redundant Directional Control 审中-公开
公开(公告)号：US20200231297A1
公开(公告)日：2020-07-23
申请号：US16790676
申请日：2020-02-13
申请人： Textron Innovations Inc.
发明人： Paul K. Oldroyd , John Richard McCullough
IPC分类号： B64D31/10 , B64C29/02 , B64C39/02 , B64C27/52 , G05D1/00 , B64D27/26 , G05D3/00 , B64D27/24 , G05D1/10
摘要： An aircraft has an airframe with a two-dimensional distributed thrust array attached thereto having a plurality of propulsion assemblies that are independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto that is operable to tilt about first and second axes responsive to first and second actuators. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector. Responsive to a thrust vector error of a first propulsion assembly, the flight control system commands at least a second propulsion assembly, that is symmetrically disposed relative to the first propulsion assembly, to counteract the thrust vector error, thereby providing redundant directional control for the aircraft.

82. 发明申请

US20200062381A1 PROPELLER IMPACT DETECTION AND FORCE REDUCTION 审中-公开
公开(公告)号：US20200062381A1
公开(公告)日：2020-02-27
申请号：US16673579
申请日：2019-11-04
申请人： Kitty Hawk Corporation
发明人： Christopher Scott Saunders
IPC分类号： B64C27/00 , B64C27/08 , B64D31/10 , B64D45/00 , B64D17/80
摘要： A commanded control signal is compared against an adaptive control signal in order to detect a rotor strike by a rotor included in an aircraft, wherein the adaptive control signal is associated with controlling the rotor and the adaptive control signal varies based at least in part on the commanded control signal and state information associated with the rotor. In response to detecting the rotor strike, a control signal to the rotor is adjusted in order to reduce a striking force associated with the rotor.

83. 发明授权

US10507908B2 Propeller impact detection and force reduction 有权
公开(公告)号：US10507908B2
公开(公告)日：2019-12-17
申请号：US16249645
申请日：2019-01-16
申请人： Kitty Hawk Corporation
发明人： Christopher Scott Saunders
IPC分类号： B64C27/06 , B64C27/00 , B64C27/08 , B64D31/10 , B64D45/00 , B64D17/80
摘要： A commanded control signal is compared against an adaptive control signal in order to detect a rotor strike by a rotor included in an aircraft, wherein the adaptive control signal is associated with controlling the rotor and the adaptive control signal varies based at least in part on the commanded control signal and state information associated with the rotor. In response to detecting the rotor strike, a control signal to the rotor is adjusted in order to reduce a striking force associated with the rotor.

84. 发明申请

US20190127076A1 Methods and Aircraft for Optimized Reverse Thrust Operation During Landing 审中-公开
公开(公告)号：US20190127076A1
公开(公告)日：2019-05-02
申请号：US15801486
申请日：2017-11-02
申请人： The Boeing Company
发明人： Christopher M. Hodges , Melissa L. Gates
IPC分类号： B64D31/10 , B64D45/00
摘要： An example method of optimizing reverse thrust operation on an aircraft having two or more engines while landing the aircraft is described. The method includes operating the two or more engines on the aircraft in a reverse idle during a landing rollout of the aircraft, responsively causing deployment of a thrust reverser on each of the engines causing a first reverse idle thrust for slowing the aircraft, monitoring each of the engines for failure of deployment of the thrust reverser, and based on detection of a failure of deployment of a respective thrust reverser on one of the engines, operating the one of the engines on the aircraft at a second reverse idle thrust optimized for a direction of an applied thrust of the one of the engines. The second reverse idle thrust is lower than the first reverse idle thrust.

85. 发明授权

US10246183B1 Propeller impact detection and force reduction 有权
公开(公告)号：US10246183B1
公开(公告)日：2019-04-02
申请号：US15877047
申请日：2018-01-22
申请人： Kitty Hawk Corporation
发明人： Christopher Scott Saunders
IPC分类号： B64C27/00 , B64C27/08 , B64D31/10 , B64D45/00 , B64D17/80
摘要： A commanded control signal is compared against an adaptive control signal in order to detect a rotor strike by a rotor included in an aircraft, wherein the adaptive control signal is associated with controlling the rotor and the adaptive control signal varies based at least in part on the commanded control signal and state information associated with the rotor. In response to detecting the rotor strike, a control signal to the rotor is adjusted in order to reduce a striking force associated with the rotor.

86. 发明申请

US20180297712A1 Aircraft having Redundant Directional Control 审中-公开
公开(公告)号：US20180297712A1
公开(公告)日：2018-10-18
申请号：US15972431
申请日：2018-05-07
申请人： Bell Helicopter Textron Inc.
发明人： Paul K. Oldroyd , John Richard McCullough
IPC分类号： B64D31/10 , B64C29/02 , B64C39/02 , B64C27/52 , G05D1/00 , B64D27/24 , B64D27/26 , G05D3/00
摘要： An aircraft has an airframe with a two-dimensional distributed thrust array attached thereto having a plurality of propulsion assemblies that are independently controlled by a flight control system. Each propulsion assembly includes a housing with a gimbal coupled thereto that is operable to tilt about first and second axes responsive to first and second actuators. A propulsion system is coupled to and operable to tilt with the gimbal. The propulsion system includes an electric motor having an output drive and a rotor assembly having a plurality of rotor blades that rotate in a rotational plane to generate thrust having a thrust vector. Responsive to a thrust vector error of a first propulsion assembly, the flight control system commands at least a second propulsion assembly, that is symmetrically disposed relative to the first propulsion assembly, to counteract the thrust vector error, thereby providing redundant directional control for the aircraft.

87. 发明申请

US20170253342A1 ASYMMETRY-PROOF MULTI-ENGINE AIRCRAFT 审中-公开
公开(公告)号：US20170253342A1
公开(公告)日：2017-09-07
申请号：US15061425
申请日：2016-03-04
申请人： Embraer S.A.
发明人： Ierko DE MAGALHÃES GOMES
IPC分类号： B64D31/10 , B64D27/24 , B64D27/12 , B64D41/00 , B64D45/00
CPC分类号： B64D31/10 , B64D27/12 , B64D27/24 , B64D41/00 , B64D2027/026 , Y02T50/62
摘要： An aircraft compensates for asymmetry of engine failure by drawing part of the energy produced by the still-operating engine to generate thrust at the tip of the opposite wing. For example, the left engine drives its own thrust on the left wing, but a portion of the energy the left engine produces is delivered at a propeller at the tip of right wing. Similarly, the right engine drives its own thrust on the right wing, but a portion of the energy the right engine produces is delivered at a propeller at the tip of the left wing. In this way, every pair of engines and opposite tip thrust generators are intrinsically balanced. In the event of one engine failure, no yaw moment will be noticed.

88. 发明申请

US20170158342A1 AERIAL VEHICLE 审中-公开
公开(公告)号：US20170158342A1
公开(公告)日：2017-06-08
申请号：US15367247
申请日：2016-12-02
申请人： NIPPON SOKEN, INC. , DENSO CORPORATION
发明人： Hiroki ISHII , Koji KAWASAKI , Takenori MATSUE , Shinji ANDOU , Hiroyasu BABA
IPC分类号： B64D31/10 , B64C27/08 , G05D1/04 , G05D1/08 , G07C5/08
CPC分类号： B64D31/10 , B64C27/08 , B64C39/024 , B64C2201/024 , B64C2201/027 , B64C2201/108 , B64C2201/141 , G05D1/0072 , G05D1/042 , G05D1/0816 , G07C5/0808
摘要： In an aerial vehicle, a malfunction determiner determines whether there is a malfunction in one of thrusters of the aerial vehicle. A flight controller activates the thrusters, and controls the output of each of the thrusters. The flight controller deactivates, when it is determined that there is a malfunction in one of the thrusters as a malfunctioned thruster, the malfunctioned thruster. The flight controller deactivates a selected thruster in the thrusters; the selected thruster being paired to the malfunctioned thruster, and controls the active thrusters except for the deactivated thrusters in all the thrusters to make the flight attitude of the aerial vehicle stable. The flight controller controls the active thrusters to cause the aerial vehicle to land while maintaining the flight attitude of the aerial vehicle being stable.

89. 发明授权

US09505488B2 Energy protection method and device for an aircraft 有权
标题翻译：飞机的能量保护方法和装置
公开(公告)号：US09505488B2
公开(公告)日：2016-11-29
申请号：US14922420
申请日：2015-10-26
申请人： Airbus Operations (SAS)
发明人： Marie-Claire Moune
IPC分类号： B64C15/02 , B64D25/00 , B64D31/06 , B64D31/10
CPC分类号： B64C15/02 , B64D25/00 , B64D31/06 , B64D31/10
摘要： An energy protection device comprising an activation unit for, in a low energy situation, automatically activating an energy protection function comprising automatically engaging an autothrust and automatically controlling the engines of the aircraft for the engines to supply a maximum thrust, an auxiliary monitoring unit configured to perform a monitoring to detect an absence of activation of a protection mode by at least one of the engines of the aircraft although an activation command has been transmitted, and a disconnection unit to automatically disconnect the autothrust in case of the detection of such a situation, a disconnection of the autothrust resulting in the triggering of the protection function being stopped.
摘要翻译：一种能量保护装置，包括用于在低能量情况下自动启动能量保护功能的激活单元，所述能量保护功能包括自动地接合自相关并自动地控制用于发动机的飞机的发动机以提供最大推力;辅助监控单元，执行监视以检测飞机的至少一个发动机的保护模式的激活，尽管已经发送了激活命令，以及断开单元，在检测到这种情况的情况下自动断开自动停止，自动停止导致触发保护功能的断开被停止。

90. 发明授权

US4143839A Apparatus for combating rolling movements of aircraft 失效
标题翻译：用于对付飞机滚动运动的装置
公开(公告)号：US4143839A
公开(公告)日：1979-03-13
申请号：US828765
申请日：1977-08-29
申请人： Oleg K. Antonov , Valentin T. Maslov , Alexei F. Voitko
发明人： Oleg K. Antonov , Valentin T. Maslov , Alexei F. Voitko
IPC分类号： B64D31/10 , B64C13/16
CPC分类号： B64D31/10
摘要： The apparatus operates to prevent the rolling of an aircraft having an even number of propulsion units when one of the propulsion units stops operating due to a breakdown. Spoilers are mounted on the outboard wings. Each spoiler has an individual drive connected to a power circuit via a control valve which, in turn, is functionally associated with a failure detector of the propulsion unit disposed on the outboard wing opposite to that on which the respective spoiler is mounted. The apparatus is provided with an apparatus that is brought into action automatically, so as to counteract the rolling tendency of an aircraft when one of its propulsion units fails, or with a manual control for correcting the glidepath during landing, dissipating the lift and applying the aerodynamic braking during the landing roll.
摘要翻译：当其中一个推进单元由于击穿而停止运行时，该装置用于防止具有偶数个推进单元的飞行器的滚动。飞镖安装在外侧翼上。每个扰流器具有通过控制阀连接到电力回路的单独驱动器，该控制阀又与设置在与安装相应扰流器的外侧翼上的外侧翼上的推进单元的故障检测器功能相关联。该装置具有自动启动的装置，以抵消当其推进装置之一发生故障时飞机的滚动倾向，或用于在着陆期间校正滑行道的手动控制，消散电梯和施加着陆卷期间的空气动力学制动。

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