摘要
本文研究载人飞船三自由度标准返回轨道的设计方法。基本的设计思想是在返回坐标系中建立飞船返回轨道运动方程，用非等值的速度滚动角γｖ（ｔ）使飞船再入过载均匀化及减小标准返回轨道与升力失控时自旋轨道的航程差，并引入侧向制导思想解决γｖ（ｔ）的反向问题。仿真中用二重迭代方法确定有关参数，避免了参数选择的盲目性。仿真计算表明，本文提出的设计思想具有良好的实用价值。
in this paper, a design method for the 3-degree standard return trajectory of the manned spaceship is studied. The basic design concept is to first set up the motion equations of it's return trajectory in the return coordinate system, then to homogenize the reentry overload and diminish the flight range difference between the standard trajectory and the self-spin one when the lift is out of control by using non-constant bank angle γv (t). The lateral guidance idea is introduced to determine the sign of γv(t). Finally, the theoretical analysis and numerical results show that the design scheme proposed has good practical value.
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
1996年第3期63-67,共5页
Journal of National University of Defense Technology
