国防科技大学学报2017，Vol.39Issue(1)：58-66,9.DOI:10.11887/j.cn.201701010
高超声速飞行器纵向平面滑翔飞行制导控制方法
Longitudinal integrated guidance and control scheme for hypersonic vehicle in glide phase
摘要
Abstract
A longitudinal integrated guidance and control scheme for the hypersonic vehicle in glide phase was designed based on the dynamic surface control method and the sliding mode control theory.The translational rotational dynamic and kinematical equations in the longitudinal plane were denoted;the desired velocity slope angle was derived based on the predictor corrector of the longitudinal range;the relations of the velocity slope angle, angle of attack, and the pitch rate were established.The dynamic surface control, the terminal sliding model and the second-order sliding mode control methods were adopted to implement the longitudinal integrated guidance and control scheme;the commanded angle of attack and elevon fins were analytically solved by using the GHV's aerodynamic model having partial derivative matrix forms.The effectiveness and robustness of the newly proposed longitudinal integrated guidance and control scheme was validated.Moreover, the characteristics of flight phases before and after the quasi equilibrium glide phase were discussed and the problems with respect to the guidance and control system design were analyzed.关键词
高超声速飞行器/制导控制系统/动态面控制/准平衡滑翔/纵向平面Key words
hypersonic vehicle/guidance and control system/dynamic surface control/quasi equilibrium glide/longitudinal plane分类
航空航天引用本文复制引用
王建华,刘鲁华,王鹏,汤国建..高超声速飞行器纵向平面滑翔飞行制导控制方法[J].国防科技大学学报,2017,39(1):58-66,9.基金项目
国家自然科学基金资助项目(61104200) （61104200）
