-
公开(公告)号：EP3193230B1
公开(公告)日：2020-01-01
申请号：EP17151148.8
申请日：2017-01-12
-
公开(公告)号：EP3197772A1
公开(公告)日：2017-08-02
申请号：EP15851070.1
申请日：2015-09-21
IPC分类号： B64C27/10 , B64C27/467 , B64C27/54
CPC分类号： B64C27/57 , B64C27/10 , B64C27/22 , B64C27/605
摘要： A system and method for counteracting a rotor moment of one or more rotors of a coaxial rotor helicopter includes receiving signals with a processor indicative of a displacement command from a controller during a flight maneuver; receiving one or more signals with the processor from a sensor indicative of an airspeed and air density for the helicopter; determining a commanded rate of acceleration for the helicopter during the flight maneuver; and adjusting with one or more control servos a cyclic pitch for the one or more rotors to counteract the rotor moment during the flight maneuver.
摘要翻译： 用于抵消同轴转子直升机的一个或多个转子的转子力矩的系统和方法包括：利用处理器接收信号，所述处理器在飞行操纵期间指示来自控制器的位移命令; 利用处理器从指示直升机的空速和空气密度的传感器接收一个或多个信号; 确定飞行操纵期间直升机的命令加速速率; 以及利用一个或多个控制伺服机构调整所述一个或多个转子的循环间距以抵消飞行操纵期间的转子力矩。
-
公开(公告)号：EP3264215A1
公开(公告)日：2018-01-03
申请号：EP17177924.2
申请日：2017-06-26
IPC分类号： G05D1/10
CPC分类号： B64C27/025 , B64C27/006 , B64C27/57 , B64D45/00 , B64D45/04 , B64D45/06 , B64D2045/0085 , G05D1/0858 , G05D1/105
摘要： A method of automating entry of an aircraft into autorotation includes detecting a loss of engine power, analyzing a sensed height and sensed airspeed of the aircraft, determining an adjusted position of one or more control surfaces of the aircraft in response to the sensed height and sensed airspeed, and automatically moving the one or more control surfaces to the adjusted position.
摘要翻译： 使飞机自动进入自转的方法包括检测发动机功率的损失，分析飞机的感测高度和感测空速，响应于感测高度确定飞机的一个或多个控制表面的调整位置，并感测 空速，并自动将一个或多个控制表面移动到调整后的位置。
-
公开(公告)号：EP3201087A2
公开(公告)日：2017-08-09
申请号：EP15848071.5
申请日：2015-09-29
IPC分类号： B64C27/82
摘要： A method of controlling a rotary wing aircraft includes accelerating the aircraft in a fore direction independently of cyclic control of the main rotor and pitch of the aircraft.
摘要翻译： 提供了一种包括机身，延伸尾部和反向旋转同轴主转子组件的飞机，该同轴主旋翼组件包括具有上部叶片的上部转子组件和具有下部叶片的下部转子组件。 上叶片和下叶片中的一个中的第一天线以及上叶片和下叶片中的另一个中的第二天线。 将激励信号施加到第一天线的振荡器。 一种叶片接近监测器，用于监测激励信号的大小和来自第二天线的输出信号，以确定上叶片和下叶片之间的距离。
-
-
公开(公告)号：EP3126231B1
公开(公告)日：2019-01-02
申请号：EP14888084.2
申请日：2014-04-02
-
公开(公告)号：EP2976260B1
公开(公告)日：2018-02-14
申请号：EP14807547.6
申请日：2014-03-12
IPC分类号： B64C27/635 , B64C27/57 , B64C27/605
CPC分类号： B64C27/57 , B64C27/605 , B64C27/635
摘要： A control system for a rotor assembly includes a plurality of sensors configured to detect a lead-lag rate of each rotor blade of a plurality of rotor blades rotatable around a shaft and a flight control computer configured to generate lead-lag compensation signals based on the detected lead rate and lag rate of each rotor blade to control each rotor blade.
-
公开(公告)号：EP3099574A1
公开(公告)日：2016-12-07
申请号：EP15742916.8
申请日：2015-01-26
CPC分类号： G05D1/0858 , B64C27/10
摘要： Embodiments are directed to generating, by a processing device, a feedback command for an aircraft based on a reference input and an output response of the aircraft, and analyzing, by the processing device, the feedback command to allocate control to a plurality of control surfaces over a plurality of separate frequency bands.
-
9.发明公开
公开(公告)号：EP3004899A1
公开(公告)日：2016-04-13
申请号：EP14836717.0
申请日：2014-05-22
IPC分类号： G01P5/00
摘要： Embodiments are directed to determining, by a computing device comprising a processor, at least one parameter associated with a rotorcraft, obtaining, by the computing device, a profile of a vibration associated with the operation of the rotorcraft based on the at least one parameter, determining, by the computing device, an amplitude of the vibration using the profile, and determining, by the computing device, an airspeed of the rotorcraft based on amplitude.
摘要翻译： 实施例涉及通过包括处理器的计算设备来确定与旋翼航空器相关联的至少一个参数，由计算设备基于至少一个参数获得与旋翼航空器的操作相关联的振动的轮廓， 由所述计算装置使用所述轮廓确定所述振动的幅度，以及由所述计算装置根据振幅确定所述旋翼航空器的空速。
-
公开(公告)号：EP2976260A1
公开(公告)日：2016-01-27
申请号：EP14807547.6
申请日：2014-03-12
IPC分类号： B64C27/635
CPC分类号： B64C27/57 , B64C27/605 , B64C27/635
摘要： A control system for a rotor assembly includes a plurality of sensors configured to detect a lead-lag rate of each rotor blade of a plurality of rotor blades rotatable around a shaft and a flight control computer configured to generate lead-lag compensation signals based on the detected lead rate and lag rate of each rotor blade to control each rotor blade.
-
-
-
-
-
-
-
-
-
搜索结果
13 条记录 (耗时 0.011 秒)
