Fast trajectory-orbit unified design for spacecrafts

Jie-gang WANG; Jia-lun PU; Yuan LI; Ming-ze WANG

doi:10.3788/OPE.20182612.2923

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Fast trajectory-orbit unified design for spacecrafts

Micro/Nano Technology and Fine Mechanics | 更新时间：2020-07-05

- Fast trajectory-orbit unified design for spacecrafts
- Optics and Precision Engineering Vol. 26, Issue 12, Pages: 2923-2929(2018)
- 作者机构：
  
  哈尔滨工业大学航天学院, 黑龙江哈尔滨 150001
- 作者简介：
- 基金信息：
- DOI：10.3788/OPE.20182612.2923
  CLC： V412.4
- Received：02 July 2018，
  
  Accepted：30 August 2018，
  
  Published：25 December 2018
- 稿件说明：
移动端阅览
Jie-gang WANG, Jia-lun PU, Yuan LI, et al. Fast trajectory-orbit unified design for spacecrafts[J]. Optics and precision engineering, 2018, 26(12): 2923-2929.
DOI：

Jie-gang WANG, Jia-lun PU, Yuan LI, et al. Fast trajectory-orbit unified design for spacecrafts[J]. Optics and precision engineering, 2018, 26(12): 2923-2929. DOI： 10.3788/OPE.20182612.2923.

摘要

为了提高空间飞行器的快速入轨能力，满足空间飞行器弹道/轨道设计工作的快速、精确、可靠要求，对空间飞行器弹道/轨道一体化快速设计方法进行了研究。首先，对空间飞行器进行动力学建模，分析弹道/轨道一体化设计需要满足的过程约束和终端约束，给出空间飞行器的飞行时序；为保证求解效率，针对传统的弹道设计数值求解算法进行了创新改进，综合应用改进牛顿迭代法、Broyden秩1方法和最速下降方法，保证算法在初值不准的条件下仍能快速收敛；最后，研究了一种新的内外多层次求解策略，同时将弹道段和轨道段分轮进行一体化设计，进一步提高了算法的可靠性。仿真结果表明，本文所研究的空间飞行器弹道/轨道一体化快速设计方法可在30 s内实现弹道/轨道设计，设计精度为0.5 m。该设计算法可靠、快速、精确，可应用于空间飞行器的快速入轨设计中。

Abstract

To improve the rapid response of a spacecraft and ensure that its trajectory-orbit unified design meets the requirements of speed

accuracy

and reliability

a rapid trajectory-orbit unified design method for spacecrafts was studied. First

the dynamic model of a spacecraft was constructed. The process and terminal constraints required for a spacecraft's trajectory-orbit unified design were analyzed and its flight procedure was given. Then

the traditional trajectory design numerical solution was improved. Through application of the improved Newtonian

Broyden rank-1

and steepest descent methods

the convergence of the methods was ensured when the initial value wad incorect. Finally

a multi-step and multi-layer method was considered

and the algorithm was further improved. The simulation result reveals that the proposed rapid trajectory-orbit unified design method for a spacecraft can be executed in 30 s

and the design orbital precision is 0.5 m. The algorithm is reliable

rapid

and accurate

and can be applied to trajectory-orbit unified designs of rapid-response spacecrafts.

关键词

Keywords

references

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