一种组合动力飞行器上升制导方法  

Ascent Guidance Method for Combined Powered Vehicle

作　　者：李栩进 韩鹏鑫[2] 丁嘉元 褚光远 LI Xu-jin;HAN Peng-xin;DING Jia-yuan;CHU Guang-yuan(China Academy of Launch Vehicle Technology,Beijing 100076,China;Aerospace Business Department,China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]中国运载火箭技术研究院空天业务部,北京100076

出　　处：《计算机仿真》2023年第6期38-41,106,共5页Computer Simulation

摘　　要：针对组合动力飞行器上升制导精度低、鲁棒性差的问题,提出了一种基于模型预测控制思想的轨迹跟踪制导方法。方法利用预测模型、滚动优化和反馈校正的策略,预测干扰因素对系统的影响,将原强非线性目标函数转换为线性目标函数,结合在线滚动优化获得上升最优制导指令,实现了存在不确定性情况下组合动力飞行器对基于高度-速度剖面的标称轨迹的高精度制导。以某组合动力飞行器为研究对象进行了纵向平面内仿真分析,仿真结果验证了上述方法在气动参数拉偏情况下,系统能够较好的跟踪期望轨迹。Aiming at the problems of low ascent guidance accuracy and poor robustness of combined powered ve-hicles,a trajectory tracking guidance method based on model predictive control is proposed.The predictive model,rolling optimization and feedback correction strategy are used to predict the influence of interference factors on the system,convert the original strong non-linear objective function,and combines with online rolling optimization to ob-tain the ascending optimal guidance command,which realizes the existence high-precision guidance of the composite-powered vehicle to the desired H-V trajectory under uncertainty.A longitudinal in-plane simulation analysis is car-ried out with the combined powered vehicle as the research object.The simulation results demonstrate that the pro-posed method can track better the desired trajectory when the aerodynamic parameters are biased.

关 键 词：组合动力飞行器 上升制导 模型预测控制 轨迹跟踪 

分 类 号：V411.8[航空宇航科学与技术—航空宇航推进理论与工程]