A composite optimization method for separation parameters of large-eccentricity pico-satellites

Lai TENG; Zhong-he JIN

doi:10.1631/FITEE.1700416

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A composite optimization method for separation parameters of large-eccentricity pico-satellites

Regular Papers | Updated：2022-05-19

- A composite optimization method for separation parameters of large-eccentricity pico-satellites
- 一种大偏心皮卫星分离参数复合优化方法
- Frontiers of Information Technology & Electronic Engineering Vol. 19, Issue 5, Pages: 685-698(2018)
- Affiliations：
  
  School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China
- Author bio：
  
  [ "Lai TENG, E-mail: tenglai@zju.edu.cn" ]
- Funds：
- DOI：10.1631/FITEE.1700416
  CLC： TH122
- Received：24 June 2017，
  
  Revised：2018-;5-;4，
  
  Published：2018-05
- Accepted：
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Lai TENG, Zhong-he JIN. A composite optimization method for separation parameters of large-eccentricity pico-satellites[J]. Frontiers of Information Technology & Electronic Engineering, 2018, 19(5): 685-698.
DOI：

Lai TENG, Zhong-he JIN. A composite optimization method for separation parameters of large-eccentricity pico-satellites[J]. Frontiers of Information Technology & Electronic Engineering, 2018, 19(5): 685-698. DOI： 10.1631/FITEE.1700416.

摘要

航天飞行器的分离参数直接影响它的飞行轨迹，如果分离参数超过它能承受的极限，则飞行器难以调整飞行姿态，可能造成飞行器偏离轨道或坠毁。提出一种将角速度与外矩结合的大偏心皮卫星分离参数复合优化方法。通过改变弹性发射装置位置，在分离机构变化较小情况下，有效控制飞行器弹出过程。给出了角速度偏差的原因和不可信的优化结果，并对不可信的优化结果进行分析。通过地面无重力试验对该优化方法进行验证。仿真和试验结果表明，该优化方法能有效优化大偏心皮卫星的分离参数。该方法特别适用于固定和非稳定状态弹性参数、各种弹性装置的分布以及难以校正姿态的大偏心航天飞行器，在实际应用中具有通用性和易操作性。

Abstract

A spacecraft's separation parameters directly affect its flying trace. If the parameters exceed their limits

it will be difficult to adjust the flying attitude of the spacecraft

and the spacescraft may go off-track or crash. In this paper

we present a composite optimization method

which combines angular velocities with external moments for separation parameters of large-eccentricity pico-satellites. By changing the positions of elastic launch devices

the method effectively controls the popping process under the condition of less change in the separation mechanism. Finally

the reasons for deviation of angular velocities and unreliable optimization results are presented and analyzed. This optimization method is proved through a ground test which offsets the gravity. Simulation and test results show that the optimization method can effectively optimize the separation parameters of large-eccentricity pico-satellites. The proposed method adapts particularly to the fixed and non-stable status elastic parameters

the distribution of all kinds of elastic devices

and large-eccentricity spacecrafts for which attitude corrections are difficult. It is generally applicable and easy to operate in practical applications.

关键词

Keywords

references

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