摘要
为提高受干扰条件下飞行任务成功率,以逃逸飞行器为研究对象,给出了基于误差传播评估弹道鲁棒性的标称轨迹生成办法和线性二次调节器(LQR)控制律制导方法。整个系统建立在飞行器精确动力学模型之上,针对逃逸飞行器工况特点,在被动段利用误差传播法快速打靶寻找满足任务需求的标称轨迹,在飞行主动段采用LQR制导跟踪标称轨迹。以上2种方法从系统的误差线性化模型推导得出,具有一定共通性。仿真结果表明,通过快速打靶规划出的飞行指令,可使得逃逸飞行器在受干扰环境下有55%的概率完成飞行目标,轨迹具有一定鲁棒性;采用LQR控制律,实现了对速度、射高等多变量的跟踪。
To improve the success rate of flight mission under disturbed conditions,a nominal trajectory generation method based on error propagation was proposed to evaluate the trajectory robustness and the LQR(Linear Quadratic Regulator)guidance method.Considering the unique flight condition of the escape vehicle,a precise dynamic system model was built.In the passive phase,the error propagation method was used for quick shooting to find the satisfactory nominal trajectory,which would be tracked later by using the LQR guidance law in the powered phase.The above two methods were both derived from the error linearization model and consequently shared some similarity.A simulation example was designed and the results showed that,via the fast shooting skill,the flight instructions could ensure 55%probability of mission completion in disturbed environment.Meanwhile,by means of LQR control law,the multi-variable tracking of the speed and shooting height was realized.
作者
李臻
杨彪
荆武兴
高长生
常武权
LI Zhen;YANG Biao;JIN Wuxing;GAO Changsheng;CHANG Wuquan(Department of Aerospace Engineering,Harbin Institute of Technology,Harbin 150001,China;Beijing Institute of Aerospace Systems Engineering,Beijing 100076,China)
出处
《载人航天》
CSCD
北大核心
2019年第6期699-708,共10页
Manned Spaceflight
关键词
逃逸飞行器
误差传播法
LQR控制
轨迹设计
escape vehicle
error propagation method
LQR control
trajectory design
