具有迎角/过载限制器的俯仰增稳系统控制律的研究

THE STUDY OF THE CONTROL LAWS OF PITCH STABILITY AUGMENTATION SYSTEM WITH ANGLE-OF-ATTACK/NORMAL ACCELERATION LIMITER

本文以JJ-6飞机为例,研究了采用具有迎角/过载限制器的俯仰增稳系统对该机在大迎角下稳定性和操纵性的影响.并根据该机在大迎角下的偏离/失速运动机理,探讨系统中限制器边界值确定的原则。研究结果表明,该系统具有抗偏离/失速的能力,进而可以防止尾旋发生。但在大迎角下过大的横侧操纵,飞机仍能进入尾旋运动。

In the paper.the stability and control of JJ-6 aircraft are studied when the aircraft is installed a pitch stability augmentation system with angle-of-attack/normal acceleration limiter at high angle of attack. The boundary value of various limiters are determined in the control system based on the mechanism of departure /stall entry. Results of the investigation show that JJ-6 aircraft possess the capability of departure resistant,and can prevent the aircraft from entering into a spin. But the aircraft could srill enter into a spin at high angle of attack during large lateral-direction command.