基于虚拟中心引力场方法的航天器转移轨道设计

袁建平; 孙冲; 方群

doi:10.6052/0459-1879-14-112

基于虚拟中心引力场方法的航天器转移轨道设计

袁建平^1,2,
孙冲^1,2,
方群^1,2

1.
西北工业大学航天学院, 西安 710072
2. 航天飞行动力学技术国家级重点实验室, 西安 710072

基金项目: 国家自然科学基金资助项目(11272255).

详细信息

作者简介:
孙冲,博士研究生,主要研究方向:航天飞行动力学与控制.E-mail: sunc2011100269@126.com

中图分类号: V412.4+1
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出版历程
- 收稿日期: 2014-05-07
- 修回日期: 2014-07-31
- 刊出日期: 2015-01-17

SPACECRAFT'S TRANSFER ORBIT DESIGN BASED ON THE VIRTUAL CENTRAL GRAVITY FIELD METHOD

1.
College of Astronautics, Northwestern Polytechnic University, Xi'an 710072, China
2. National Key Laboratory of Aerospace Flight Dynamics, Xi'an 710072, China

Funds: The project was supported by the National Natural Science Foundation of China (11272255).

摘要

摘要: 空间机动技术是实现空间操作任务的基础,具有重要的研究价值. 研究了连续推力作用下航天器转移轨道设计问题,提出了一种基于虚拟中心引力场的轨道设计方法. 该方法有两大特点:(1) 能够将机动轨道设计问题转化为虚拟中心引力场参数的优化问题,简化了设计过程;(2) 对轨道形状或推力方向、大小不做任何假定,能够应用于一般情况下的机动轨道设计. 将该方法应用于航天器二维和三维的转移轨道设计,并和形状方法进行了对比分析. 仿真结果分析表明,采用该方法简化了轨道设计过程,为航天器快速轨道设计提供了新思路.
- 轨道机动 /
- 转移轨道 /
- 连续推力 /
- 中心引力场
Abstract: The space maneuver technology is the basis of space mission operation. In this paper, a novel method named virtual central gravitational field method for continuous thrust maneuver trajectory design for the spacecraft is proposed, which can decrease the number of trajectories' parameters. Because there is no assumption in this approach, it can be used in general case. This approach applies in orbit transfer in both 2-D and 3-D spaces, and the results show that in the same condition, the required thrust acceleration and energy cost are smaller than that of shape-based methods.
- trajectory maneuver /
- transfer orbit /
- continuous thrust /
- central gravitational field

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参考文献(9)

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