摘要
针对高超声速滑翔飞行器,提出了一种基于在线气动参数修正的预测制导方法.研究了再入过程中受到的各种飞行约束,给出了多约束下控制量设计的基本方案.分析了传统预测制导法在落点预测过程中存在的气动参数偏差影响,引入综合升力系数与综合阻力系数,并对其进行在线参数估计以及参数修正,以提高制导方法的适应性.基于气动参数修正方法,完成了纵向与横侧向制导律设计.设定较大的轴向力、法向力系数组合偏差对该方法进行了验证,并考虑再入初始条件和再入气动参数的不确定性,进行了蒙特卡洛仿真.结果表明:预测制导法中引入气动参数的在线估计与修正环节,可保证其制导精度,尤其对再入过程的气动扰动具有较强的适应能力.
A new predictive reentry guidance algorithm based on aerodynamic parameter online correction for hypersonic gliding vehicles was presented. The constraints of reentry flight were studied, and a basic pro- gram for controller design was given. The aerodynamic parameters＇ errors in the process of traditional target prediction were analyzed. With the new composite parameters for lift and drag, the method for aerodynamic parameter online correction was established. Online estimation and online correction were used to improve the adaptivity of the predictive reentry guidance. The longitudinal guidance law and lateral guidance law were then designed, and proved to work well with large aerodynamic disturbance. To test the capacity of the guidance method, the Monte Carlo simulation was used. The results indicate that the predictive guidance method with parameter online correction has high guidance precision and good robustness for the aerodynamic disturbance.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2013年第7期853-857,共5页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金资助项目(90916003)
高等学校学科创新引智计划111工程资助项目(B07009)
关键词
高超声速飞行器
再入制导
预测制导
参数估计
在线修正
hypersonic vehicles
reentry guidance
predictive guidance
parameter estimation
onlinecorrection
