基于C/GMRES模型预测控制的滑翔段轨迹跟踪研究  

Study on Gliding Trajectory Tracking Based on C/GMRES Model Predictive Control

作　　者：闫瑞 泮斌峰[1] YAN Rui;PAN Binfeng(School of Astronautics,Northwestern Polytechnical University,Xi′an 710072,China)

机构地区：[1]西北工业大学航天学院,西安710072

出　　处：《载人航天》2020年第4期508-515,共8页Manned Spaceflight

基　　金：国家自然科学基金(11672234)。

摘　　要：针对使用非线性模型预测控制方法进行再入飞行器滑翔段轨迹跟踪时计算量大、耗时长的问题,采用了一种基于延拓法的广义极小残差数值算法(C/GMRES)快速解算非线性模型预测控制中的优化问题。首先给出了滑翔段纵向运动方程;然后采用基于C/GMRES算法的非线性模型预测控制律进行纵向轨迹跟踪并离线规划航向角误差走廊;最后采用倾侧反转策略改变倾侧角的符号以实现横向轨迹控制。仿真结果表明:C/GMRES算法的引入有效解决了传统方法求解两点边值问题时耗时长的问题,同时该轨迹跟踪控制律对初始状态扰动和动态干扰具有较强的鲁棒性。Tracking the gliding path of the reentry vehicle with nonlinear model predictive control method needs large amount of calculation and is time-consuming.A C/GMRES(Continuation/Generalized Minimal Residual)numerical algorithm based on the continuation method was adopted to solve the optimization problem in nonlinear model predictive control.The longitudinal motion equation of the gliding phase was given,then the nonlinear model predictive control law based on C/GMRES algorithm was used to track the longitudinal trajectory,while the heading error corridor was planned offline.The bank angle inversion strategy was adopted to realize the lateral trajectory control by changing the symbol of the bank angle.The simulation results showed that the introduction of C/GMRES algorithm could effectively solve the long time-consumption problem of the traditional methods in solving the two-point boundary value.At the same time,the trajectory tracking control law also had strong robustness to initial state disturbances and dynamic disturbances.

关 键 词：C/GMRES算法 模型预测控制 轨迹跟踪 再入飞行器 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]