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1. 发明申请

US20130168501A1 PRIMARY FLIGHT CONTROLS 有权
标题翻译：主要飞行控制
公开(公告)号：US20130168501A1
公开(公告)日：2013-07-04
申请号：US13534193
申请日：2012-06-27
申请人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
发明人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
IPC分类号： B64C27/625
CPC分类号： B64C27/625 , B64C13/503 , B64C27/64 , B64C27/68 , Y02T50/44
摘要： Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).
摘要翻译：用于直升机的主和/或尾转子（4）的主飞行控制（10），其具有在线控和/或飞越控制之间的电 - 机械接口和用于控制力的液压伺服致动器（8）朝向所述主和/或尾部转子控制器（4）的放大。对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械联动装置（7）连接到一个电动马达（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）和其输出端（30）的一个机械连杆（7）和一个电动机（5）是直接驱动型的类型，所述电动马达（5）的位置）和所述电动马达（5）传递到所述液压伺服驱动器（8）的扭矩与所述电动马达（5）的功率消耗有关。

2. 发明授权

US08684314B2 Emergency piloting by means of a series actuator for a manual flight control system in an aircraft 有权
标题翻译：通过飞机上的手动飞行控制系统的串联执行器进行紧急驾驶
公开(公告)号：US08684314B2
公开(公告)日：2014-04-01
申请号：US13417667
申请日：2012-03-12
申请人： Bruno Chaduc , Patrick Hellio , Bernard Gemmati , Karsten Krok
发明人： Bruno Chaduc , Patrick Hellio , Bernard Gemmati , Karsten Krok
IPC分类号： G05D1/00
CPC分类号： B64C13/30 , B64C13/42 , B64C27/58 , Y02T50/44
摘要： For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
摘要翻译：对于飞机（1）的手动飞行控制系统（7）的紧急驾驶，在弹性连接装置（26）断开的情况下，上游控制装置（8）对系列的电子控制单元（29）进行授权致动器（21）。输出枢转象限（25）由定心杆（22）承受阻塞和定心作用。在系统断裂的情况下，输出枢转象限（25）形成用于串联致动器（21）的轴承点，使得紧急控制致动翼面（11）。

3. 发明授权

US08342455B2 Method of assisting piloting, piloting assistance means, and a piloting assistance device for a rotorcraft using said piloting assistance means to implement said piloting assistance method 有权
标题翻译：使用所述驾驶辅助装置辅助驾驶，驾驶辅助装置和用于旋翼航空器的驾驶辅助装置的方法来实施所述驾驶辅助方法
公开(公告)号：US08342455B2
公开(公告)日：2013-01-01
申请号：US12814687
申请日：2010-06-14
申请人： Jean-Marie Allieta , Bruno Chaduc , Jean-Francois Lafisse , Olivier Honnorat
发明人： Jean-Marie Allieta , Bruno Chaduc , Jean-Francois Lafisse , Olivier Honnorat
IPC分类号： G05D1/00
CPC分类号： B64C27/68 , B64C27/56
摘要： The present invention relates to a device and method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control (10) for controlling a rotor (20, 21) via at least one linkage (35), during which method an additional force is generated by at least one piloting assistance means (100) mechanically linked to the linkage (35), the additional force being a function of the position of the flight control (10) and of an instantaneous force as measured on the linkage (35).
摘要翻译：本发明涉及一种辅助驾驶飞行器的驾驶的装置和方法，所述旋翼航空器具有用于经由至少一个联动装置（35）控制转子（20,21）的飞行控制装置（10），在该方法中，附加的力由与所述连杆机构（35）机械连接的至少一个引导辅助装置（100）产生，所述附加力是所述飞行控制器（10）的位置和在所述连杆机构（35）上测量的瞬时力的函数，。

4. 发明申请

US20110031346A1 METHOD OF ASSISTING PILOTING, PILOTING ASSISTANCE MEANS, AND A PILOTING ASSISTANCE DEVICE FOR A ROTORCRAFT USING SAID PILOTING ASSISTANCE MEANS TO IMPLEMENT SAID PILOTING ASSISTANCE METHOD 有权
标题翻译：辅助引导方法，引导辅助装置以及用于使用专用辅助辅助装置的转子的引导辅助装置来实现所述的引导辅助方法
公开(公告)号：US20110031346A1
公开(公告)日：2011-02-10
申请号：US12814687
申请日：2010-06-14
申请人： Jean-Marie Allieta , Bruno Chaduc , Jean-Francois Lafisse , Olivier Honnorat
发明人： Jean-Marie Allieta , Bruno Chaduc , Jean-Francois Lafisse , Olivier Honnorat
IPC分类号： B64C27/00
CPC分类号： B64C27/68 , B64C27/56
摘要： The present invention relates to a device and method of assisting the piloting of a rotorcraft, the rotorcraft having a flight control (10) for controlling a rotor (20, 21) via at least one linkage (35), during which method an additional force is generated by at least one piloting assistance means (100) mechanically linked to the linkage (35), the additional force being a function of the position of the flight control (10) and of an instantaneous force as measured on the linkage (35).
摘要翻译：本发明涉及一种辅助驾驶飞行器的驾驶的装置和方法，所述旋翼航空器具有用于经由至少一个联动装置（35）控制转子（20,21）的飞行控制装置（10），在该方法中，附加的力由与所述连杆机构（35）机械连接的至少一个引导辅助装置（100）产生，所述附加力是所述飞行控制器（10）的位置和在所述连杆机构（35）上测量的瞬时力的函数，。

5. 发明授权

US08888036B2 Primary flight controls 有权
标题翻译：主要飞行控制
公开(公告)号：US08888036B2
公开(公告)日：2014-11-18
申请号：US13534193
申请日：2012-06-27
申请人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
发明人： Bruno Chaduc , Boris Grohmann , Christophe Tempier
IPC分类号： B64C11/00 , B64C27/68 , B64C27/64 , B64C27/625 , B64C13/50
CPC分类号： B64C27/625 , B64C13/503 , B64C27/64 , B64C27/68 , Y02T50/44
摘要： Primary flight controls (10) for main and/or tail rotors (4) of helicopters with electro-mechanical interface between any of fly-by-wire and/or fly-by-light controls and hydraulic servo actuators (8) for control force amplification towards said main and/or tail rotor controls (4). For each of the main and/or tail rotor controls (4) there is provided but one of the hydraulic servo actuators (8), connected by one mechanical linkage (7) to one electro motor (5), said one hydraulic servo actuator (8) being of the type having the one mechanical linkage (7) connected to its input (29) and its output (30) and the one electro motor (5) being of the direct drive type, the position of said electro motor (5) having a reference to said one mechanical linkage (7) and the torque delivered by said electro motor (5) to the hydraulic servo actuator (8) being related to the power consumption of said electro motor (5).
摘要翻译：用于直升机的主和/或尾转子（4）的主飞行控制（10），其具有在线控和/或飞越控制之间的电 - 机械接口和用于控制力的液压伺服致动器（8）朝向所述主和/或尾部转子控制器（4）的放大。对于每个主转子控制器和/或尾部转子控制器（4），只有一个液压伺服致动器（8）通过一个机械联动装置（7）连接到一个电动马达（5），所述一个液压伺服致动器 8）是具有连接到其输入端（29）和其输出端（30）的一个机械连杆（7）和一个电动机（5）是直接驱动型的类型，所述电动马达（5）的位置）和所述电动马达（5）传递到所述液压伺服驱动器（8）的扭矩与所述电动马达（5）的功率消耗有关。

6. 发明申请

US20120241563A1 EMERGENCY PILOTING BY MEANS OF A SERIES ACTUATOR FOR A MANUAL FLIGHT CONTROL SYSTEM IN AN AIRCRAFT 有权
标题翻译：用于飞机上的手动飞行控制系统的系列执行机构的紧急引导
公开(公告)号：US20120241563A1
公开(公告)日：2012-09-27
申请号：US13417667
申请日：2012-03-12
申请人： Bruno Chaduc , Patrick Hellio , Bernard Gemmati , Karsten Krok
发明人： Bruno Chaduc , Patrick Hellio , Bernard Gemmati , Karsten Krok
IPC分类号： G05D1/00
CPC分类号： B64C13/30 , B64C13/42 , B64C27/58 , Y02T50/44
摘要： For emergency piloting of a manual flight control system (7) of an aircraft (1), in the event of flexible connection means (26) breaking, an upstream control device (8) takes authority over the electronic control unit (29) of series actuator (21). An output pivoting quadrant (25) is subjected by a centering rod (22) to a blocking and centering action. In the event of the system breaking, the output pivoting quadrant (25) forms a bearing point for the series actuator (21), so that an emergency control actuate a airfoil surface (11).
摘要翻译：对于飞机（1）的手动飞行控制系统（7）的紧急驾驶，在弹性连接装置（26）断开的情况下，上游控制装置（8）对系列的电子控制单元（29）进行授权致动器（21）。输出枢转象限（25）由定心杆（22）承受阻塞和定心作用。在系统断裂的情况下，输出枢转象限（25）形成用于串联致动器（21）的轴承点，使得紧急控制致动翼面（11）。

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