航天器最优再入轨迹的选择分析

THE ANALYSIS OF REENTY TRAJECTORY OF MANNED SPACE VECHCLE

本文研究的目的是想获得具有最大有效载荷的航天器最优再入轨迹。返回段航天器的最大有效载荷等价于航天器离轨点所耗燃料质量与热防护系统（ＴＰＳ）质量之和达极小。文中把最大有效载荷的再入轨迹分三种情况作了分析：航天器ＴＰＳ质量不确定时，通过返回轨迹优化来获得航天器的最大有效载荷，并选择确定相应ＴＰＳ的质量；ＴＰＳ质量已确定时，通过再入轨迹优化来获得航天器的最大有效载荷；ＴＰＳ质量足够大时，通过多次穿越大气层来获得航天器的最大有效载荷。本文的结论可为航天器再入轨迹与ＴＰＳ的一体化选择提供思路。

The paper stuidied how to obtain the maximum payload by the optimal reentry trajectories under the following circumastances: When TPS mass of space vehicle is not determined, the maximum payload is obtained by the optimal return trajectory design, then TPS mass is determined; when TPS mas of the space vehicle is determined, the maximum payload is obtained by the design of optimal reentry trafetory; when the TPS mass is enough large, the maximum payload of the vehicle can be obtained by multipe-pass atmosphere. The conclusion of the paper provides a design method for the reentry trajectory/TPS of the vehicle.