摘要
Two-impulse control is used for concomitant orbital control. Based on concomitant motion sate transferring equation, analytic solution of two-impulse concomitant orbital transfer is derived, the control variables are optimized by means of genetic algorithm, and optimal transfer time and trajectories are gained.
| 源语言 | 英语 |
|---|---|
| 页(从-至) | 398-400 |
| 页数 | 3 |
| 期刊 | Yuhang Xuebao/Journal of Astronautics |
| 卷 | 25 |
| 期 | 4 |
| 出版状态 | 已出版 - 7月 2004 |
指纹
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