rendezvous guidance

基本解释

This paper presents the approaches and practical theoretical models on synthetic orbit maneuver during long distance guidance stage of space rendezvous.
文章研究了空间交会远程导引阶段综合变轨问题的变轨策略方法和实用理论模型。
The other scenarios illustrate that the guidance algorithm can ensure a close range rendezvous motion in any direction, at any time with the fuel economy and under the constraints as well.
算法能够以较省的燃料消耗实现轨道面内任意方向、任意时间内满足约束的近距离交会。
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The structural form of three kinds of optimum rendezvous guidance laws are presented. Simultaneously the equations of parameters depended an optimum rendezvous guidance laws of three kinds are given.
除给出了最优交会体制导律的结构形式外，还提供了求解最优交会制导律的参数方程组。