类IXV飞行器初期再入制导与姿态控制方法研究  

Reentry Guidance and Control Method for Class-IXV Aircraft

作　　者：黄盘兴 何英姿[1,2] 杨鸣 郭敏文[1,2] HUANG Panxing;HEYingzi;YANG Ming;GUO Minwen(Beijing Institute of Control Engineering,Beijing 100190,China;Na-tional Key Laborator of Science and Technology on Space Intelligent Control,Beijing 100094,China.)

机构地区：[1]北京控制工程研究所,北京100190 [2]空间智能控制技术国家级重点实验室,北京100094

出　　处：《空间控制技术与应用》2018年第3期22-27,42,共7页Aerospace Control and Application

基　　金：国家自然科学基金资助项目(61403030)~~

摘　　要：针对类IXV飞行器无翼式升力体构型及采用RCS/尾襟翼组合控制特点,研究其初期再入段的高精度制导与姿态控制方法.设计带过程约束的数值预测-校正制导律以提高制导系统的鲁棒性及精确性;根据其执行机构配置特点,设计基于RCS的航向控制律及基于RCS/气动舵的纵、横向复合控制律,并采用鲁棒伺服LQR技术进行控制参数快速设计.通过蒙特卡洛打靶仿真来验证算法的精度及鲁棒性.The class-IXV aircraft is a lifting body without wings,and is actuated through the combination of two body flaps mounted at the aft windward side of the vehicles and RCS thrusters. The accurate re-entry guidance and attitude control approaches are studied in this paper. Firstly,a numerical predictor-corrector guidance law with flight path constraints is designed to enhance the robustness and accuracy of guidance system. Secondly,a hybrid control law is proposed,with the yaw axis performed by the RCS thrusters,and both the longitudinal and lateral axes performed by the RCS and aerodynamic flaps. Furthermore,robust servo LQR method is used to design the control parameters rapidly. Finally,Monte Carlo simulation is presented to validate the high accuracy and robustness of the proposed algorithm.

关 键 词：IXV 初期再入 数值预测-校正制导 复合控制 

分 类 号：V448[航空宇航科学与技术—飞行器设计]