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公开(公告)号：US08032269B2
公开(公告)日：2011-10-04
申请号：US11947040
申请日：2007-11-29
CPC分类号： B64C27/006
摘要： A flight control system which detects a failure of a flight control surface and performs at least one action in response to the detected failure.
摘要翻译： 一种飞行控制系统，其检测飞行控制表面的故障并且响应于检测到的故障执行至少一个动作。
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公开(公告)号：US5265825A
公开(公告)日：1993-11-30
申请号：US936187
申请日：1992-08-26
CPC分类号： G05D1/0055 , G05D1/0858
摘要： A helicopter engine fuel control anticipates sudden changes in engine power demand during yaw inputs to thereby minimize engine and main rotor speed droop and overspeed during yaw maneuvers. The rate (121,123) of yaw control (107) position change generates (110) a yaw component (104) of a helicopter fuel control (52) fuel command signal (70). The magnitude of the yaw component is also dependant upon the rate of yaw control position change (703). The fuel command signal yaw component (104) is overridden (113,115) when rotor decay rate (209,217) has been arrested during a sharp left hover turn (216); when the yaw component is removing fuel (239) during rotor droop (238); and when the yaw component is adding fuel (228) during rotor overspeed (227).
摘要翻译： 直升机发动机燃料控制预计在偏航输入期间发动机功率需求的突然变化，从而使偏航操纵期间的发动机和主转子速度下降和超速最小化。 偏航控制（107）位置变化的速率（121,123）产生（110）直升机燃料控制（52）燃料指令信号（70）的偏航分量（104）。 偏航分量的大小也取决于偏航控制位置变化的速度（703）。 当旋转衰减速率（209,217）在急停的左悬停转弯（216）期间被停止时，燃料指令信号偏航分量（104）被覆盖（113,115）。 当偏转分量在转子下垂期间移除燃料（239）时; 并且当偏转分量在转子超速期间添加燃料（228）（227）时。
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公开(公告)号：US5971325A
公开(公告)日：1999-10-26
申请号：US996692
申请日：1997-12-23
CPC分类号： G05D1/0033 , G05D1/0858
摘要： A control system for small unmanned rotorcraft compensates for vehicle pitch control saturation caused by the need for sudden vehicle pitch attitude correction, in turn often caused by wind gusts. The rotorcraft has a pitch-variable rotor system responsive to a vehicle pitch servo command for cyclically controlling rotor pitch and responsive to a collective servo command for collectively controlling rotor pitch. A compensating signal derived from the unlimited vehicle pitch servo command signal is cross-connected to the unlimited collective servo command signal to compensate for pitch control saturation, typically by reducing the magnitude of the resulting collective servo command signal. The compensating signal is derived by passing the unlimited vehicle pitch servo command signal through a dead band which responds as the signal approaches saturation and by preferably also then providing high and low frequency shaping to that signal.
摘要翻译： 用于小型无人驾驶旋翼飞机的控制系统补偿由于需要突然的车辆俯仰姿态校正而引起的车辆俯仰控制饱和度，反过来又常常由阵风引起。 旋翼航空器具有响应于车辆俯仰伺服指令的变桨转子系统，用于循环地控制转子间距并且响应于集体伺服命令来共同控制转子间距。 从无限车辆俯仰伺服命令信号导出的补偿信号与无限制的集体伺服命令信号交叉连接，以通常通过减小所得到的集体伺服命令信号的幅度来补偿桨距控制饱和。 补偿信号是通过将无限车辆俯仰伺服指令信号传递通过在信号接近饱和时作出响应的死区而导出的，并且优选地还可以向该信号提供高和低频整形。
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公开(公告)号：US07931231B2
公开(公告)日：2011-04-26
申请号：US12026560
申请日：2008-02-06
IPC分类号： B64C27/57
CPC分类号： B64C13/503 , B64C11/305 , B64C27/54 , B64D31/06 , G05B13/026
摘要： A flight control system and method which determines an expected power required data in response to a flight control command of the at least one model following control law and utilizes the expected power required data to perform at least one action to control an engine speed.
摘要翻译： 一种飞行控制系统和方法，其响应于所述至少一个模型的飞行控制命令响应控制定律来确定预期功率需求数据，并利用所述预期功率需求数据来执行至少一个动作来控制发动机速度。
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公开(公告)号：US20090012658A1
公开(公告)日：2009-01-08
申请号：US11947040
申请日：2007-11-29
CPC分类号： B64C27/006
摘要： A flight control system which detects a failure of a flight control surface and performs at least one action in response to the detected failure.
摘要翻译： 一种飞行控制系统，其检测飞行控制表面的故障并且响应于检测到的故障执行至少一个动作。
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公开(公告)号：US20080283671A1
公开(公告)日：2008-11-20
申请号：US12026560
申请日：2008-02-06
IPC分类号： B64C13/16
CPC分类号： B64C13/503 , B64C11/305 , B64C27/54 , B64D31/06 , G05B13/026
摘要： A flight control system and method which determines an expected power required data in response to a flight control command of the at least one model following control law and utilizes the expected power required data to perform at least one action to control an engine speed.
摘要翻译： 一种飞行控制系统和方法，其响应于所述至少一个模型的飞行控制命令响应控制定律来确定预期功率需求数据，并利用所述预期功率需求数据来执行至少一个动作来控制发动机速度。
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公开(公告)号：US5265826A
公开(公告)日：1993-11-30
申请号：US935764
申请日：1992-08-26
CPC分类号： G05D1/0055 , G05D1/0858
摘要： A helicopter engine fuel control anticipates changes in main rotor torque in response to lateral cyclic pitch commands, to thereby minimize engine and main rotor speed droop and overspeed during left and right roll maneuvers. A fuel compensation signal (100,101) is summed with a helicopter fuel control (52) fuel command signal (67) in response both to a lateral cyclic pitch command signal (LCP) (107) from a pilot operated cyclic pitch control exceeding a left or right threshold magnitude (201,210) and a total lateral cyclic pitch command signal (TCP) (108) from a lateral cyclic pitch control system exceeding a left or right threshold magnitude (202,207,215,220). The magnitude of the fuel compensation signal is dependant upon the direction of TCP and LCP, e.g., left or right, and helicopter roll acceleration (115). Alternatively, the magnitude and duration of the fuel compensation signal is dependant upon the rate of change in commanded lateral cyclic pitch (107,400,407). A limiter (120) limits the magnitude of the fuel compensation signal. The fuel compensation signal is overridden (127,125,103) when it is increasing fuel flow ( 303) during rotor overspeed (128,301), and when it is decreasing fuel flow (311) if rotor acceleration (130,133) is negative (310) during rotor droop (128,301).
摘要翻译： 直升机发动机燃料控制预测主旋翼扭矩响应于横向循环俯仰命令的变化，从而使左右滚动机动中的发动机和主转子速度下降和超速最小化。 燃料补偿信号（100,101）与直升机燃料控制（52）燃料指令信号（67）相加，响应于来自超过左边的先导操作的循环音调控制的横向循环音调指令信号（LCP）（107） 右侧阈值幅度（201,210）和来自横向循环音调控制系统的总横向循环音调指令信号（TCP）（108）超过左阈值或右阈值幅度（202,207,215,220）。 燃料补偿信号的大小取决于TCP和LCP的方向，例如左或右，以及直升机滚动加速度（115）。 或者，燃料补偿信号的幅度和持续时间取决于指令的横向循环间距的变化率（107,400,407）。 限制器（120）限制燃料补偿信号的大小。 当转子超速（128,301）期间增加燃料流量（303）时，以及如果在转子下降期间转子加速度（130,133）为负（310）时，燃料补偿信号被减少（127,125,103） 128,301）。
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