摘要
研究的目的是解决飞行器飞行空域和飞行状态大范围快速变化时姿态控制系统的适应性问题。采取的方法是首先通过某一大气飞行器的传递函数计算分析,找出对传递函数幅相特性影响比较大的关键动力学系数,再通过对关键动力学系数的全气动表变化规律研究,设计出姿态控制系统的动静态增益随M,α,β和q的变化规律,从而实现了动静态增益在整个飞行状态下的自适应调节,大大提高了姿态控制系统的裕度和适应性。
The research aim of this paper is to resolve the adaption of the attitude control about atmosphere vehicle, whose flight airspace and condition is changing widely and rapidly. The approach is to discover the key dynamics coefficient by calculating and analyzing transfer function, design out the varietional rule of gain along with M, α ,β and q through studying the key dynamics coefficient of all table of aerodynamic parameter. The redundance and adaption of the attitude control system is enhanced greatly by the mothed of the adaptive adjustment in all flight status.
出处
《航天控制》
CSCD
北大核心
2008年第4期3-7,共5页
Aerospace Control
关键词
大气飞行器
姿态控制
自适应增益调节
Atmosphere vehicle
Attitude control
Adptive adjustment of control gain
