根据飞行器椭圆弹道的性质、飞行器再入条件、球面几何和不动点原理给出了理想弹道的计算算法。
Baced on the properties of elliptical trajectory, the reentry conditions of the vehicles, spherical geometry, and the fixed-point theorem, an algorithm for the ideal trajectory is proposed.
对登月飞船在指定轨道终点及多约束条件下两次再入轨道的优化设计进行了研究。
The optimal design of the trajectory for the standard twice reentry of mooncraft under the conditions of the trajectory endpoint set and multiply objective constraints in this paper.
在现有再入段解析方法的基础上，考虑更为贴近实际的条件因素，求得一组新的弹道导弹再入弹道解析解。
A new analytic solution of the ballistic missiles reentry trajectory is presented by considering some more actual factors on the basis of the existing analytic solution.
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