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低推力航天器的初始轨迹设计,考虑到态度约束
Zichen Fan1, Weiqin Ke2, Ji Qi3
1School of Astronautics, Harbin Institute of Technology, Harbin, 150001, China. fanzichenhit@163.com.
Scientific reports
|August 30, 2024
概括
这项研究引入了航天器的新轨道优化算法,通过考虑态度约束来提高深空任务的燃料效率. 该方法提高了低推力航天器的初始轨迹设计精度.
科学领域:
- 航空航天工程 航空航天工程
- 天体动力学是指天体动力学.
- 太空任务设计空间任务设计
背景情况:
- 航天器燃料,特别是用于态度控制,对于深空任务至关重要.
- 现有的轨道优化方法可能无法完全考虑态度约束,影响任务效率.
研究的目的:
- 为低推力航天器开发基于形状的轨迹优化算法,该算法包含了态度约束.
- 提高用于深空探索的初始转移轨迹设计的准确性.
主要方法:
- 开发了一种基于形状的新型轨迹优化算法.
- 该算法考虑了推进加速方向变化的速率和范围上的约束.
- 进行了模拟,比较了带有和没有姿态约束的轨迹.
主要成果:
- 拟议的算法通过整合态度约束来产生更准确的传输轨迹.
- 考虑到航天器的态度约束对于有效的初始转移轨迹设计至关重要.
- 该方法在深空任务中对高精度轨迹优化具有重要意义.
结论:
- 开发的算法通过包括态度约束来增强低推力航天器的轨迹优化.
- 这种方法对于提高深空探索任务的精度和成功至关重要.
- 准确的初始轨迹设计对于高效的燃料使用和任务完成至关重要.
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