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1. 发明授权

EP0641425B1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL 失效
标题翻译：综合火力和飞行控制与方位角和俯仰控制直升机
公开(公告)号：EP0641425B1
公开(公告)日：1996-09-18
申请号：EP93911145.6
申请日：1993-05-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholas, D. , DRYFOOS, James, B. , KELLER, James, F.
IPC分类号： F41G3/22 , G05D1/08
CPC分类号： F41G3/22 , G05D1/085 , G05D1/0858
摘要： A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920), the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference. During integration of the fire control system and the flight control system, the flight control system is made less sensitive to small pilot command stick inputs below a stick input threshold magnitude, so that small or inadvertent pilot commanded yaw and pitch maneuvers will not affect the yaw and pitch attitude reference commanded by the fire control system azimuth and elevation commands. However, intended pilot commanded yaw and pitch maneuvers (70) maintain full authority at all times.

2. 发明授权

EP0763222B1 INERTIAL VELOCITY COMMAND SYSTEM 失效
标题翻译：惯性速度指令系统
公开(公告)号：EP0763222B1
公开(公告)日：1998-07-22
申请号：EP95919762.5
申请日：1995-05-04
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： GOLD, Phillip, J. , FOGLER, Donald, L., Jr. , DRYFOOS, James, B.
IPC分类号： G05D1/10
CPC分类号： G05D1/0858

3. 发明授权

EP0600988B1 High speed turn coordination for rotary wing aircraft 失效
标题翻译：在高速下用于旋翼式飞机的协调偏离方向。
公开(公告)号：EP0600988B1
公开(公告)日：1995-09-27
申请号：EP92917911.7
申请日：1992-07-31
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： SKONIECZNY, Joseph, P. , FOGLER, Donald, L., Jr. , GOLD, Philipp, J. , KELLER, James, F. , DRYFOOS, James, B.
IPC分类号： G05D1/08
CPC分类号： G05D1/085 , G05D1/0858
摘要： A helicopter flight control system (21) includes a model following control system architecture which automatically provides a coordinating yaw command signal to the helicopter tail rotor to coordinate helicopter flight during a banked turn. The control system processes information from a variety of helicopter sensors (31) in order to provide the coordinating yaw command signal on an output line (72) to the tail rotor (20) of the helicopter.

4. 发明公开

EP0641425A1 HELICOPTER INTEGRATED FIRE AND FLIGHT CONTROL HAVING AZIMUTH AND PITCH CONTROL 失效
标题翻译：集成火灾与方位角和俯仰控制直升机飞行控制。
公开(公告)号：EP0641425A1
公开(公告)日：1995-03-08
申请号：EP93911145.0
申请日：1993-05-07
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： FOWLER, Donald, W. , LAPPOS, Nicholas, D. , DRYFOOS, James, B. , KELLER, James, F.
IPC分类号： B64C13 , B64C27 , F41G3 , G05D1
CPC分类号： F41G3/22 , G05D1/085 , G05D1/0858
摘要： A fire control system (55) azimuth command and elevation command provides a flight control system attitude reference in response to operation of the flight control system in a coupled aiming mode. The coupled aiming mode is engaged in response to the continuous operation of a pilot switch (920), the azimuth command and elevation command being below respective threshold magnitudes (940, 941), and the operation of the fire control system (55). During operation in the coupled aiming mode, the azimuth command and elevation command replace the yaw attitude feedback error signal and pitch attitude error signal, respectively, as the aircraft attitude reference. During integration of the fire control system and the flight control system, the flight control system is made less sensitive to small pilot command stick inputs below a stick input threshold magnitude, so that small or inadvertent pilot commanded yaw and pitch maneuvers will not affect the yaw and pitch attitude reference commanded by the fire control system azimuth and elevation commands. However, intended pilot commanded yaw and pitch maneuvers (70) maintain full authority at all times.

5. 发明公开

EP0601073A1 IMPROVED MODEL FOLLOWING CONTROL SYSTEM 失效
标题翻译：改进后的模型在控制系统之后
公开(公告)号：EP0601073A1
公开(公告)日：1994-06-15
申请号：EP92919085.0
申请日：1992-08-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： WRIGHT, Stuart, C. , DRYFOOS, James, B.
IPC分类号： B64C13 , G05D1
CPC分类号： B64C13/503 , G05D1/0825 , G05D1/0858
摘要： Un système de commande de vol d'un aérodyne incluant des lois de commande suivant un modèle comprend une logique et des algorithmes améliorés afin de limiter l'erreur entre une valeur paramétrique désirée provenant de la sortie d'un modèle et une valeur paramétrique réelle. Une telle logique peut fonctionner pour détecter la quantité de ladite erreur paramétrique et limiter la quantité de l'erreur si elle dépasse une valeur prédéterminée. La différence entre la limite prédéterminée et l'erreur réelle est renvoyée au modèle de sorte que la sortie du modèle est ajustée pour que l'erreur entre les valeurs paramétriques désirée et réelle ne dépasse pas la valeur prédéterminée.
摘要翻译：包括模型控制法则的航空飞行控制系统包括改进的逻辑和算法，以限制来自模型输出的期望参数值与实际参数值之间的误差。这种逻辑可以操作来检测所述参数误差的量并且如果误差量超过预定值则限制误差量。预定极限和实际误差之间的差值返回到模型，以便调整模型的输出，使得期望参数值和实际参数值之间的误差不超过预定值。

6. 发明公开

EP0763222A1 INERTIAL VELOCITY COMMAND SYSTEM 失效
标题翻译：惯性速度指令系统
公开(公告)号：EP0763222A1
公开(公告)日：1997-03-19
申请号：EP95919762.0
申请日：1995-05-04
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： GOLD, Phillip, J. , FOGLER, Donald, L., Jr. , DRYFOOS, James, B.
IPC分类号： B64C13 , B64C27 , G05D1
CPC分类号： G05D1/0858
摘要： A velocity command system is provided with a velocity stabilization mode wherein aircraft flight path referenced velocities are determined with respect to an inertial frame of reference, the flight path referenced velocities are held constant during pilot commanded yaw maneuvers so that the aircraft maintains a fixed inertial referenced flight path regardless of the pointing direction of the aircraft. Velocity control with respect to an inertial frame of reference is accomplished by controlling the aircraft flight path based on aircraft body referenced commanded lateral and longitudinal acceleration and based on aircraft body referenced lateral and longitudinal centrifugal acceleration. Operation in the velocity stabilization mode is provided in response to the manual activation of the velocity stabilization mode by the pilot, provided that the aircraft is already operating in the ground speed mode and the aircraft is not in a coordinated turn.
摘要翻译：速度指令系统被提供有速度稳定模式，其中飞行器飞行路线参考速度相对于惯性参考系确定，在飞行员命令的偏航操纵期间，飞行路径参考速度保持恒定，使得飞行器保持固定的惯性参考不管飞机的指向方向如何。相对于惯性参考系的速度控制是通过基于飞机本体参考命令的横向和纵向加速度并且基于飞机本体参考的横向和纵向离心加速度来控制飞机飞行路径来实现的。响应于飞行员手动启动速度稳定模式，提供速度稳定模式下的操作，前提是飞机已经以地面速度模式运行并且飞机不处于协调转弯。

7. 发明授权

EP0601073B1 IMPROVED MODEL FOLLOWING CONTROL SYSTEM 失效
标题翻译：改进后的模型在控制系统之后
公开(公告)号：EP0601073B1
公开(公告)日：1995-11-22
申请号：EP92919085.8
申请日：1992-08-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： WRIGHT, Stuart, C. , DRYFOOS, James, B.
IPC分类号： G05D1/08
CPC分类号： B64C13/503 , G05D1/0825 , G05D1/0858
摘要： An aircraft flight control system including model following control laws includes improved logic and algorithms to limit the error between a desired parameter value from the output of a model and an actual parameter value. Such logic is operable to sense the amount of said parameter error and to limit the amount of the error if it exceeds a predetermined value. The difference between the predetermined limit and the actual error is fed back to the model such that the output of the model is adjusted so that the error between the desired and actual parameter values does not exceed the predetermined value.
摘要翻译：包括模型跟随控制法则的飞机飞行控制系统包括改进的逻辑和算法，以限制模型输出的期望参数值与实际参数值之间的误差。这种逻辑可操作用于感测所述参数错误的量并且如果错误超过预定值则限制错误的量。预定极限和实际误差之间的差值被反馈给模型，使得模型的输出被调节，使得期望参数值与实际参数值之间的误差不超过预定值。

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