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公开(公告)号：US20180222573A1
公开(公告)日：2018-08-09
申请号：US15426560
申请日：2017-02-07
发明人： Luke Gillett , Sung K. Kim
CPC分类号： B64C13/503 , B64C13/00 , B64C27/06 , B64C27/82 , G05D1/0061 , G05D1/0066 , G05D1/0077 , G05D1/0202 , G05D1/0204 , G05D1/0816 , G05D1/0858
摘要： In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes operating the rotorcraft in a speed control mode, where a speed of the rotorcraft is proportional to a pilot control command; detecting a high longitudinal acceleration condition; upon detection of the high longitudinal acceleration condition, temporarily disabling the speed control mode and stabilizing the rotorcraft while the speed control mode is disabled; and reestablishing the speed control mode when a measured longitudinal acceleration of the rotorcraft falls below a first threshold.
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公开(公告)号：US09878776B2
公开(公告)日：2018-01-30
申请号：US14278868
申请日：2014-05-15
申请人： The Boeing Company
发明人： Vedad Mahmulyin
CPC分类号： B64C13/00 , B64C5/02 , B64C9/00 , B64C13/04 , B64C13/16 , B64C13/503 , B64D43/02 , G05D1/0066
摘要： A method of controlling an elevator of an aircraft may include identifying a current stabilizer angle of incidence of a stabilizer of the aircraft. The stabilizer may include an elevator pivotably coupled to the stabilizer. The method may further include comparing the current stabilizer angle of incidence with a threshold stabilizer angle of incidence, and selecting an elevator position limit that is more restrictive if the current stabilizer angle of incidence is greater than or equal to the threshold stabilizer angle of incidence. The method may additionally include moving the elevator to a commanded elevator position that is no greater than the elevator position limit.
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公开(公告)号：US09868512B2
公开(公告)日：2018-01-16
申请号：US14440272
申请日：2013-10-29
摘要： An airplane wing comprises a main wing and a flap system that has a flap at the trailing edge of the main wing. An elongate flap track member is connected to the main wing in such a manner that it can be moved substantially in its longitudinal direction and is guided by supporting bearing elements relative to the main wing between a forward retracted position and a rearward extended position. The flap is rotatably connected to the rear end of the flap track member in such a manner that it can rotate about a rotation axis that extends substantially parallel to the trailing edge of the main wing, so that the flap moves together with the flap track member when the flap track member is moved and so that the flap can be rotated about the rotation axis mechanically independently of the movement of the flap track member. The flap system comprises an actuator system having two actuators. The first actuator is connected to the main wing and has an engagement member that engages the flap or the flap track member for moving the flap together with the flap track member so that the flap track member is move able between its retracted position and its extended position. The second actuator is connected to the flap track member so that the second actuator moves together with the flap track member when the flap track member is moved by means of the first actuator. The second actuator has an engagement member that engages the flap for rotating the flap about the rotation axis.
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公开(公告)号：US09663219B2
公开(公告)日：2017-05-30
申请号：US14807014
申请日：2015-07-23
发明人： Mathieu Carton , Pierre Debusschere , David Chabe
CPC分类号： B64C13/00 , B64D39/00 , G05D1/0607 , G05D1/0808
摘要： The system comprises at least one lift generator element that is able to modify directly the lift of the aircraft and means for defining a deflection instruction upon actuation by a pilot of the aircraft of a control column of the aircraft generating a vertical load factor control value and applying it to an elevator and simultaneously defining a command instruction and applying it to the lift generator element to generate a direct lift.
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公开(公告)号：US20160311523A1
公开(公告)日：2016-10-27
申请号：US15134711
申请日：2016-04-21
摘要： The present application relates to a pushing device, a moving mechanism and an aircraft. According to an aspect of the present application, a pushing device for a moving mechanism of an aircraft is provided, the moving mechanism including a primary moving device and an auxiliary moving device assisting the primary moving device, the pushing device including a support member and a pushing assembly supported by the support member, and the pushing assembly including a pushing element and an energy storage element. The pushing element is adapted to push a broken part of the auxiliary moving device to an offset position from a normal working position by means of energy from the energy storage element when the auxiliary moving device breaks. According to the present application, it is possible to provide an effective fault protection to the moving mechanism of the aircraft.
摘要翻译： 本申请涉及推动装置，移动机构和飞行器。 根据本申请的一个方面，提供了一种用于飞行器的移动机构的推动装置，所述移动机构包括辅助主移动装置的主移动装置和辅助移动装置，所述推动装置包括支撑构件和 推动组件，其由支撑构件支撑，并且推动组件包括推动元件和能量存储元件。 推动元件适于当辅助移动装置断裂时借助来自能量存储元件的能量将辅助移动装置的断裂部分从正常工作位置推到偏移位置。 根据本申请，可以为飞机的移动机构提供有效的故障保护。
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公开(公告)号：US20160288921A1
公开(公告)日：2016-10-06
申请号：US14675845
申请日：2015-04-01
申请人： The Boeing Company
发明人： Peter A. Padilla
CPC分类号： B64D45/0005 , B64C9/00 , B64C9/02 , B64C9/16 , B64C9/22 , B64C13/00 , B64D2045/001 , G05D1/0055
摘要： A motionless skew detection system for an aircraft is disclosed, and includes a flight control surface of an aircraft wing, two drive mechanisms for operating the flight control surface, a first load sensor and a second load sensor for each of the two drive mechanisms, and a control module. Each of the two drive mechanisms are located on opposing sides of the flight control surface and each of the two drive mechanisms include at least a first linkage including a first outer surface and a second linkage including a second outer surface. The first load sensor is disposed along the first outer surface of the first linkage and the second load sensor is disposed along the second outer surface of the second linkage. The control module is in signal communication with the first load sensor and the second load sensor of each drive mechanism.
摘要翻译： 公开了一种用于飞行器的静止偏斜检测系统，包括飞行器机翼的飞行控制表面，用于操作飞行控制表面的两个驱动机构，用于两个驱动机构中的每一个的第一负载传感器和第二负载传感器，以及 一个控制模块。 两个驱动机构中的每一个位于飞行控制表面的相对侧上，并且两个驱动机构中的每个驱动机构至少包括第一连杆，该第一连杆包括第一外表面和包括第二外表面的第二连杆。 第一负载传感器沿着第一连杆的第一外表面设置，第二负载传感器沿着第二连杆的第二外表面设置。 控制模块与每个驱动机构的第一负载传感器和第二负载传感器进行信号通信。
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7.发明授权公开(公告)号：US09459168B2
公开(公告)日：2016-10-04
申请号：US14222061
申请日：2014-03-21
申请人： Moog Inc.
CPC分类号： G01L5/22 , B64C9/16 , B64C9/20 , B64C13/00 , B64C13/34 , B64D2045/0085 , G01L5/0028 , G01N3/08
摘要： A load-sensing strut has a main body (26) having a longitudinal loading axis (A) along which an applied load is transmitted, and a load sensing member (38) arranged to carry at least a portion of the applied load when the load is within a predetermined range, wherein the load sensing member (38) includes at least one load sensor (46) generating a load signal. The strut also has a load alleviation member (36) arranged to reduce the portion of the applied load carried by the load sensing member (38) when the applied load is outside the predetermined loading range. Consequently, the load sensors exhibit greater sensitivity to incremental changes in the applied load within the predetermined range, yet the strut provides high strength and is capable of reacting to very high loads outside of the predetermined range. The strut may be used in actuating aircraft control surfaces in a high-lift system.
摘要翻译： 负载感测支柱具有主体（26），所述主体（26）具有纵向加载轴线（A），所施加的负载穿过所述纵向加载轴线（A），以及负载感测构件（38），其布置成在负载时承载所施加的负载的至少一部分 在预定范围内，其中所述负载感测构件（38）包括产生负载信号的至少一个负载传感器（46）。 支柱还具有负载减轻构件（36），其被布置成当施加的负载在预定负载范围之外时减小由负载感测构件（38）承载的施加负载的部分。 因此，负载传感器在预定范围内对所施加的负载的增量变化表现出更大的灵敏度，但是支柱提供高强度并且能够对超出预定范围的非常高的负载作出反应。 支柱可用于在高升力系统中起动飞机控制面。
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公开(公告)号：US20160023749A1
公开(公告)日：2016-01-28
申请号：US14807014
申请日：2015-07-23
发明人： Mathieu CARTON , Pierre DEBUSSCHERE , David CHABE
CPC分类号： B64C13/00 , B64D39/00 , G05D1/0607 , G05D1/0808
摘要： The system comprises at least one lift generator element that is able to modify directly the lift of the aircraft and means for defining a deflection instruction upon actuation by a pilot of the aircraft of a control column of the aircraft generating a vertical load factor control value and applying it to an elevator and simultaneously defining a command instruction and applying it to the lift generator element to generate a direct lift.
摘要翻译： 该系统包括至少一个提升发电机元件，该升降机发电机元件能够直接修改飞行器的升降机，以及用于在飞行器的飞行员致动之后定义偏转指令的装置，该飞行器的飞行器产生垂直载荷系数控制值， 将其施加到电梯并同时定义命令指令并将其施加到电梯发电机元件以产生直接电梯。
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公开(公告)号：US09097327B2
公开(公告)日：2015-08-04
申请号：US14174661
申请日：2014-02-06
申请人： NABTESCO CORPORATION
发明人： Toshiaki Ogawa , Koji Itoh , Makoto Nagashima
摘要： An actuator-link assembly includes an actuator having first and second opposing ends in order to drive a control surface of an aircraft and a link coupled to the actuator. The actuator has a rod portion having a tip end, located at first end of the actuator, said tip end pivotably attach to a control surface of an aircraft. The link includes a pair of linear portions, each having first and second opposing ends, wherein the linear portions are disposed alongside each other; a coupling portion connecting the first ends of linear portions, a fulcrum shaft attachment portion protruding from the coupling portion configured to pivotably attach to a fulcrum shaft for rotatably supporting the control surface; and an actuator attachment portion configured to pivotably attach to the second end of the actuator. A material constituting the linear portions and the coupling portion contains fiber reinforced plastic.
摘要翻译： 致动器连杆组件包括具有第一和第二相对端的致动器，以驱动飞行器的控制表面和联接到致动器的连杆。 致动器具有杆部分，其具有位于致动器的第一端处的尖端，所述尖端可枢转地附接到飞行器的控制表面。 连杆包括一对直线部分，每一个具有第一和第二相对端部，其中直线部分彼此并排配置; 连接直线部分的第一端的联接部分，从联接部分突出的支点轴安装部分，其构造成可枢转地附接到支点轴，以可旋转地支撑控制表面; 以及构造成可枢转地附接到致动器的第二端的致动器附接部分。 构成直线部分和联接部分的材料包含纤维增强塑料。
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公开(公告)号：US20150073626A1
公开(公告)日：2015-03-12
申请号：US14022623
申请日：2013-09-10
IPC分类号： B64C19/00
摘要： Embodiments are directed to receiving, by a computing device comprising a processor, at least one control input associated with an aircraft, obtaining, by the computing device, a predicted response to the at least one control input by filtering on a trim position, wherein the predicted response is based on a model of the aircraft, obtaining, by the computing device, an actual response of the aircraft to the at least one control input, comparing, by the computing device, the predicted response and the actual response, and determining, by the computing device, at least one attribute based on the comparison
摘要翻译： 实施例涉及通过包括处理器的计算设备接收与飞行器相关联的至少一个控制输入，由计算设备通过在装饰位置上进行滤波来获得对至少一个控制输入的预测响应，其中， 预测响应基于飞行器的模型，由计算设备获得飞行器对至少一个控制输入的实际响应，通过计算设备比较预测响应和实际响应， 通过计算设备，基于比较的至少一个属性
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