无尾飞机纵向控制律设计及转换瞬态研究

Longitudinal Control Law Design for Tailless Aeroplane and Research on Tranformation Status

通过对无尾飞机与常规布局飞机进行比较,针对其纵向静不稳定采用增稳系统的纵向控制律设计方案,增稳系统用法向加速度反馈信号为主反馈,并设计纵向控制律。考虑到无尾飞机在起飞离地前的纵向构型和参数与空中控制律有所不同,设计使用机轮承载开关进行控制律切换。研究升降舵舵偏角在控制律转换瞬间可能发生的幅值跳变,提出了一种减小幅值跳变的方法。

Compared with general aeroplane,tailless aeroplane has static instability in longitudinal mode.To deal with it, control law comprising Stability Augment System(SAS)is proposed of which feedback is normal acceleration signals. And longitudinal control law is designed.On the other hand,switch is used in control laws transformation,because longitudinal structure and parameters on land are different from those in air.And it would cause jump of elevator angle in the moment of transforming between two control laws.So a method to reduce amplitude jump is presented.