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31.发明授权Method and apparatus for automatically controlling aircraft flight control trim systems 有权自动控制飞机飞行控制装饰系统的方法和装置公开(公告)号：US08718839B2
公开(公告)日：2014-05-06
申请号：US12959418
申请日：2010-12-03
Applicant: Michael Louis Everett , Louis Jackson Everett , Mario Ruiz, Jr.
Inventor： Michael Louis Everett , Louis Jackson Everett , Mario Ruiz, Jr.
IPC: G05D1/00
Abstract: An automatic trim system and method is disclosed for automatically trimming a flight control surface of an aircraft. A force sensor measures a force applied by a pilot to a flight control system actuator. The length of time that the force is applied by the pilot is then timed by a timer. A trim system to reduce the applied force is included on the flight control surfaces. A processor determines if trim is required if a predetermined amount of time is exceeded based on the force sensor measurement. The processor can set the trim system to the trim required therein. An airspeed sensor is used to verify that the aircraft has sufficient speed for flight. A force sensor can be utilized to measure the input force being applied by the pilot. If a pilot input force is applied to the controls and the aircraft is in a steady state, a timer can be activated. If the force sensor continues to sense a force after the timer times for a predetermined time, the trim can be adjusted in the appropriate direction until the force sensor measures no significant pilot input force.
Abstract translation: 公开了一种用于自动修整飞机的飞行控制表面的自动装饰系统和方法。 力传感器测量由飞行员施加到飞行控制系统致动器的力。 然后由飞行员施加力的时间长度由定时器定时。 减少施加力的装饰系统包括在飞行控制表面上。 如果基于力传感器测量超过预定量的时间，则处理器确定是否需要修剪。 处理器可以将修剪系统设置为其中所需的修整。 空速传感器用于验证飞机是否具有足够的飞行速度。 力传感器可用于测量由飞行员施加的输入力。 如果飞行员输入力施加到控制器并且飞行器处于稳定状态，则定时器可以被激活。 如果力传感器在定时器持续预定时间之后继续感测到力，则可以在适当的方向上调节修整，直到力传感器不测量重要的导向输入力。
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公开(公告)号：US08052096B2
公开(公告)日：2011-11-08
申请号：US12842916
申请日：2010-07-23
Applicant: Dino A. Cerchie , Gregory E. Dockter , William Mark Hardesty
Inventor： Dino A. Cerchie , Gregory E. Dockter , William Mark Hardesty
CPC classification number: B64C39/024 , B64C13/22 , B64C13/46 , B64C13/50 , B64C2201/024 , B64C2201/146 , G05D1/0044
Abstract: An apparatus for converting a manned aircraft of a type including at least one pilot control capable of manipulation to affect operation of the aircraft for unmanned flight operations includes first and second actuators, each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, first and second clutches, each configured to selectively couple movement of the associated actuator to or from the pilot control during flight, and a vehicle controller capable of being selectively enabled during flight to operate the pilot control actuators and clutches and thereby provide unmanned operation of the aircraft, or of being disabled, thereby providing for manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.
Abstract translation: 一种用于转换类型的载人飞机的装置，包括能够操纵以影响飞行器的无人驾驶操作的至少一个先导控制的装置包括第一和第二致动器，每个致动器被配置为以第一方式选择性地提供对运动的运动或阻力，包括 线性或旋转运动，第一和第二离合器，每个离合器构造成在飞行期间选择性地将相关致动器的运动耦合到先导控制器，以及能够在飞行期间被选择性地启用以操作先导控制致动器和离合器的车辆控制器 提供飞机的无人操作或被禁用，从而提供飞机的载人操作。 第一致动器具有描述第一允许移动量的第一范围，而第二致动器具有大于第一范围的第二范围。
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公开(公告)号：US20100286847A1
公开(公告)日：2010-11-11
申请号：US12842916
申请日：2010-07-23
Applicant: Dino A. Cerchie , Gregory E. Dockter , William Mark Hardesty
Inventor： Dino A. Cerchie , Gregory E. Dockter , William Mark Hardesty
IPC: G05D1/00
CPC classification number: B64C39/024 , B64C13/22 , B64C13/46 , B64C13/50 , B64C2201/024 , B64C2201/146 , G05D1/0044
Abstract: An apparatus for converting a manned aircraft of a type including at least one pilot control capable of manipulation to affect operation of the aircraft for unmanned flight operations includes first and second actuators, each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, first and second clutches, each configured to selectively couple movement of the associated actuator to or from the pilot control during flight, and a vehicle controller capable of being selectively enabled during flight to operate the pilot control actuators and clutches and thereby provide unmanned operation of the aircraft, or of being disabled, thereby providing for manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.
Abstract translation: 一种用于转换类型的载人飞机的装置，包括能够操纵以影响飞行器的无人驾驶操作的至少一个先导控制的装置包括第一和第二致动器，每个致动器被配置为以第一方式选择性地提供对运动的运动或阻力，包括 线性或旋转运动，第一和第二离合器，每个离合器构造成在飞行期间选择性地将相关致动器的运动耦合到先导控制器，以及能够在飞行期间被选择性地启用以操作先导控制致动器和离合器的车辆控制器 提供飞机的无人操作或被禁用，从而提供飞机的载人操作。 第一致动器具有描述第一允许移动量的第一范围，而第二致动器具有大于第一范围的第二范围。
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公开(公告)号：US07784741B2
公开(公告)日：2010-08-31
申请号：US12135055
申请日：2008-06-06
Applicant: Dino A. Cerchie , Gregory E. Dockter , William Mark Hardesty
Inventor： Dino A. Cerchie , Gregory E. Dockter , William Mark Hardesty
IPC: B64C27/00
CPC classification number: B64C39/024 , B64C13/22 , B64C13/46 , B64C13/50 , B64C2201/024 , B64C2201/146 , G05D1/0044
Abstract: An apparatus for converting a manned aircraft of a type including at least one pilot control capable of manipulation to affect operation of the aircraft for unmanned flight operations includes first and second actuators, each configured to selectively provide movement or resistance to movement in a first manner including linear or rotational motion, first and second clutches, each configured to selectively couple movement of the associated actuator to the pilot control, and a vehicle controller capable of being selectively enabled to operate the pilot control actuators and clutches and thereby provide unmanned operation of the aircraft, or of being disabled, thereby providing for manned operation of the aircraft. The first actuator has a first scope describing a first amount of allowable movement, while the second actuator has a second scope larger than the first scope.
Abstract translation: 一种用于转换类型的载人飞机的装置，包括能够操纵以影响飞行器的无人驾驶操作的至少一个先导控制的装置包括第一和第二致动器，每个致动器被配置为以第一方式选择性地提供对运动的运动或阻力，包括 线性或旋转运动，第一和第二离合器，每个离合器被配置为选择性地将相关联的致动器的运动耦合到先导控制器，以及车辆控制器，其能够被选择性地启用以操作先导控制致动器和离合器，从而提供飞行器的无人操作 或被禁用，从而提供飞机的载人操作。 第一致动器具有描述第一允许移动量的第一范围，而第二致动器具有大于第一范围的第二范围。
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公开(公告)号：US20230202651A1
公开(公告)日：2023-06-29
申请号：US17561195
申请日：2021-12-23
Applicant: Textron Innovations Inc.
Inventor： Kevin Thomas Christensen , Sang Gyun Park
CPC classification number: B64C29/0033 , B64C13/18 , B64C13/22
Abstract: A flight control computer (FCC) may implement automatic rotor tilt control by gathering or receiving, as inputs, airspeed or a commanded airspeed for the aircraft, acceleration or a commanded acceleration for the aircraft, pitch attitude of the aircraft and pilot pitch bias commands for the aircraft, a rotor tilt angle, and/or the like. The FCC calculates, from the airspeed, the commanded airspeed, the acceleration, the commanded acceleration, the pitch attitude, the pilot pitch bias commands, and/or the like, a commanded rotor tilt angle for the aircraft. From the aircraft rotor tilt angle and the commanded rotor tilt angle, the FCC calculates a rotor tilt angle error for the aircraft, and from the rotor tilt angle error, calculates a rotor tilt rate command for the aircraft. The FCC outputs the resulting rotor tilt rate command to (an) aircraft flight control element actuator(s) to tilt the aircraft rotor.
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Patent Agency Ranking
公开(公告)号：US20190241252A1
公开(公告)日：2019-08-08
申请号：US16388993
申请日：2019-04-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Shyhpyng Jack Shue
CPC classification number: B64C13/22 , B64C13/04 , B64C13/20 , B64C29/0033 , B64D45/0015 , B64D45/0031 , B64D2045/0055 , G05D1/0022 , G05D1/0061 , G05D1/0858
Abstract: In some embodiments, a control manager is disposed between the rotor system and the flight control inceptor.The control manager is configured to receive control commands wirelessly from a ground control station, translate the control commands into one or more axes associated with the flight control inceptor, and transmit the translated control commands to the rotor system in place of the instructions received from the pilot via the flight control inceptor.
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公开(公告)号：US09969485B2
公开(公告)日：2018-05-15
申请号：US14901747
申请日：2014-06-27
Applicant: BAE SYSTEMS plc
Inventor： Robin William Davies
Abstract: An inceptor apparatus (10) for controlling a vehicle, in particular an aircraft comprises a control stick (15) for operation by a user and a user feedback generator (28) coupled to the control stick and configured to receive signals from a vehicle condition indicator (40) remote from the inceptor apparatus. The apparatus also has a first vehicle condition sensor (54,56) dedicated to the operation of the inceptor apparatus. In a first mode of operation, the user feedback generator (28) is operable to generate tactile feedback to the user via the control stick in dependence upon signals received from the vehicle condition indicator (40). In a second mode of operation, in the event that no signal is received from the vehicle condition indicator (40), the user feedback generator (28) is operable to generate tactile feedback to the user via the control stick in dependence upon signals received from the first vehicle condition sensor (54,56).
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公开(公告)号：US09718537B2
公开(公告)日：2017-08-01
申请号：US15012192
申请日：2016-02-01
Applicant: Airbus Operations (SAS)
Inventor： Pierre Scacchi , Matthieu Mayolle
CPC classification number: B64C13/22 , B64C13/04 , G05D1/0808
Abstract: A piloting system having a control stick configured to control the aircraft with respect to its three piloting axes, namely the pitch axis, the roll axis and the yaw axis, and an auxiliary control device configured to automatically control the aircraft during one of the following phases: a landing phase and a takeoff phase. The auxiliary control device automatically controls the aircraft with respect to at least one of the piloting axes, and the other piloting axes, which are not controlled automatically by the auxiliary control device, then being controlled manually by a pilot with the aid of the control stick.
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公开(公告)号：US09650125B2
公开(公告)日：2017-05-16
申请号：US15231650
申请日：2016-08-08
Applicant: Merlin Technology, Inc.
Inventor： Carlos E. Golborne , Ray E. Debs , Mark Marvin , John E. Mercer
CPC classification number: B64C13/22 , B64C13/04 , B64C13/18 , B64C27/04 , B64C27/56 , B64C27/57 , B64D43/00 , G01C23/00 , G01C23/005 , G05G9/047 , G05G2009/04774
Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.
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40.发明申请Method and system for controlling the flight of an aircraft with respect to the pitch axis 有权用于控制飞机相对于俯仰轴的飞行的方法和系统公开(公告)号：US20160304189A1
公开(公告)日：2016-10-20
申请号：US15096812
申请日：2016-04-12
Applicant: Airbus Operations (SAS)
Inventor： Mathieu Carton , Pierre Debusschere , Laurent Albugues
CPC classification number: B64C13/22 , B64C13/04 , B64C13/503 , G05D1/0607
Abstract: A system including a load factor control module for calculating a deflection order on manual actuation of a control column by a pilot of the aircraft and transmitting that deflection order to at least one elevator of the aircraft, a longitudinal attitude control module for maintaining the longitudinal attitude of the aircraft at a target attitude in the event of absence of manual actuation of the control column by the pilot during a flight, and a transition management module for determining and storing a present longitudinal attitude value of the aircraft at a recording moment and transmitting that longitudinal attitude value to the longitudinal attitude control module for the longitudinal attitude control module to use the longitudinal attitude value as the target attitude.
Abstract translation: 一种系统，包括负载因子控制模块，用于计算由飞行员的驾驶员手动致动控制柱的偏转顺序，并将该偏转顺序传送到飞行器的至少一个电梯;纵向姿态控制模块，用于保持纵向姿态 在飞行中由飞行员没有手动驱动控制列的情况下以目标姿态进行飞行器的过渡管理模块，以及用于在记录时刻确定和存储飞行器的当前纵向姿态值并且传送该飞行器的过渡管理模块 纵向姿态值以纵向姿态控制模块为纵向姿态控制模块，以纵向姿态值为目标姿态。
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