摘要
研究了飞回型可重复使用航天器以高超声速再入返回的最优大回转轨迹设计和控制方法,分析了飞回型航天器再入中靠气动力实现轨迹大回转的关键技术,建立了最优再入的数学模型.采用极大值原理和共轭梯度法求解最优再入大回转问题.通过仿真,得到了考虑大回转的最优再入轨迹特性及其控制规律,分析了转弯开始时刻和滚转角对再入中倾斜转弯控制特性的影响规律.探讨了高超声速大回转再入的控制方法.
Volte-face trajectory and control of fly-back reusable spacecraft in hypersonic reentry are studied. The key technology of volte-face trajectory and control realized by adjusting aerodynamic force is analyzed. Three degree-of-freedom model of glide for spacecraft reentry is funded. Based on maximum principle and conjugate gradient method, the dynamic optimization problem of spacecraft reentry is resolved. With the constraint conditions of glide stage in reentry, optimal control variables, attack angle and roll angle, are gotten to minimize the distance between the stage end point and the launch station by means of simulation. The optimal volte-face trajectory characteristics are investigated. The laws of turning-time and roll angles during reentry acting to volte-face control characteristics are studied. Spacecraft control laws for volte-face reentry motion are explored.
出处
《弹道学报》
EI
CSCD
北大核心
2005年第2期60-64,共5页
Journal of Ballistics
基金
国家863资助项目(2002AA726012)
关键词
高超声速航天器
再入
大回转
最优轨迹
hypersonic spacecraft, reentry, volte-face, optimal trajectory
