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当一个十字翼导弹在大攻角机动飞行时,由于在控制舵面的迎风处要比背风处的动压高,会产生相当大的有害力矩。这些力矩又会交叉耦合到自动驾驶仪的滚动、俯仰和偏航通道中去,因而产生了稳定性问题。设计了一种新的飞行控制系统,它用测量、控制升力和四个尾翼舵面滚动力矩,而不是控制其舵偏角的方法减小了这种无翼导弹的有害力矩。本文给出了测量的方法和系统的设计方法,同时,也给出了一个例子。与普通的系统相比,它是交叉耦合低、稳定性高的系统。
When a cross-wing missile maneuvering at a high angle of attack, a considerable amount of harmful torque is generated due to the higher dynamic pressure at the windward side of the control surface than at the leeward. These moments in turn cross-couple into the autopilot roll, pitch and yaw channels, creating stability problems. A new flight control system is designed to reduce the unwanted torque of this non-wing missile by measuring and controlling the lift force and the rolling moment of the four tail wing rudder surfaces rather than controlling their steering angles. This article gives the measurement methods and system design methods, but also gives an example. Compared with the ordinary system, it is low cross-coupling, high stability of the system.