一种大偏心皮卫星分离参数复合优化方法

滕来; 金仲和

doi:10.1631/FITEE.1700416

Your Location：

Home >

Browse articles >

一种大偏心皮卫星分离参数复合优化方法

常规文章 | Updated：2022-05-19

- 一种大偏心皮卫星分离参数复合优化方法
- A composite optimization method for separation parameters of large-eccentricity pico-satellites
- 信息与电子工程前沿（英文） 2018年19卷第5期页码：685-698
- Affiliations：
  
  School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China
- Author bio：
  
  [ "Lai TENG, E-mail: tenglai@zju.edu.cn" ]
- Funds：
  
  Project supported by the National Natural Science Foundation of China (No. 61525403)
- DOI：10.1631/FITEE.1700416
  中图分类号： TH122
- 收稿：2017-06-24，
  
  修回：2018-;5-;4，
  
  纸质出版：2018-05
- Accepted：
Scan QR Code
滕来, 金仲和. 一种大偏心皮卫星分离参数复合优化方法[J]. 信息与电子工程前沿（英文）, 2018,19(5):685-698.

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.
滕来, 金仲和. 一种大偏心皮卫星分离参数复合优化方法[J]. 信息与电子工程前沿（英文）, 2018,19(5):685-698. DOI： 10.1631/FITEE.1700416.

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

J Chao , , , ZK Wang , , , YL Zhang . . Development of the new approach of formation initialization using spring separation mechanism considering J 2 perturbation . . Adv Space Res , , 2015 . . 55 ( ( 11 ): ): 2616 - - 2627 . . DOI: 10.1016/j.asr.2015.02.019 http://doi.org/10.1016/j.asr.2015.02.019 . .

DL Cui , , , SZ Yan , , , JL Li , , , 等 . . Dynamic analysis of satellite separation considering the flexibility of interface rings . . J Aerosp Eng , , 2014 . . 229 ( ( 10 ): ): 1886 - - 1902 . . DOI: 10.1177/0954410014562012 http://doi.org/10.1177/0954410014562012 . .

DL Cui , , , JL Zhao , , , SZ Yan , , , 等 . . Analysis of parameter sensitivity on dynamics of satellite separation . . Acta Astronaut , , 2015 . . 114 ( ( 3 ): ): 22 - - 33 . . DOI: 10.1016/j.actaastro.2015.04.007 http://doi.org/10.1016/j.actaastro.2015.04.007 . .

M Fritz , , , PD Berger . . Can you relate in multiple ways . . Multiple linear regression and stepwise regression. In: Kaufmann M (Ed.), Improving the User Experience Through Practical Data Analytics. Elsevier Inc., Boston , , 2015 . . p.239 - - 269 . . DOI: 10.1016/B978-0-12-800635-1.00010-0 http://doi.org/10.1016/B978-0-12-800635-1.00010-0 . .

J Hu , , , HC Li , , , YP Zhou . . The application of Levenberg- Marquardt algorithm in the image stitching . . Telecom Mark , , 2012 . . 2 149 - - 154 . . DOI: 10.3969/j.issn.1006-6675-B.2012.02.049 http://doi.org/10.3969/j.issn.1006-6675-B.2012.02.049 . .

XZ Hu , , , XQ Chen , , , ZH Tuo , , , 等 . . Dynamics and transient perturbation analysis of satellite separation systems . . Proc Inst Mech Eng G , , 2013 . . 227 ( ( 12 ): ): 1968 - - 1976 . . DOI: 10.1177/0954410012466780 http://doi.org/10.1177/0954410012466780 . .

XZ Hu , , , XQ Chen , , , Y Zhao , , , 等 . . Optimization design of satellite separation systems based on multi-island genetic algorithm . . Adv Spac Res , , 2014a . . 53 ( ( 5 ): ): 870 - - 876 . . DOI: 10.1016/j.asr.2013.12.021 http://doi.org/10.1016/j.asr.2013.12.021 . .

XZ Hu , , , XQ Chen , , , ZH Tuo , , , 等 . . Simplified metrics of elastic potential energy for spacecraft separation dynamics . . Acta Astronaut , , 2014b . . 102 151 - - 155 . . DOI: 10.1016/j.actaastro.2014.05.028 http://doi.org/10.1016/j.actaastro.2014.05.028 . .

XZ Hu , , , XQ Chen , , , Y Zhao , , , 等 . . Active subspace approach to reliability and safety assessments of small satellite separation . . Acta Astronaut , , 2017 . . 131 159 - - 165 . . DOI: 10.1016/j.actaastro.2016.10.042 http://doi.org/10.1016/j.actaastro.2016.10.042 . .

WH Huang , , , DQ Cao , , , ZY Han . . Advances and trends in dynamics and control of spacecrafts . . Adv Mech , , 2012 . . 42 ( ( 4 ): ): 367 - - 394 . . DOI: 10.6052/1000-0992-11-171 http://doi.org/10.6052/1000-0992-11-171 . .

T Iwasa , , , Q Shi , , , S Ando , , , 等 . . Simplified SRS prediction method for pyroshock source of V-band clamp separation devices . . 48 th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conf , , 2007 . . p.1 - - 12 . . DOI: 10.2514/6.2007-2020 http://doi.org/10.2514/6.2007-2020 . .

C Jiang , , , ZK Wang , , , YL Zhang . . Angular velocity depressing method of constrained and centroid biased on-orbit separation . . Acta Aeronaut Astronaut Sin , , 2015 . . 36 ( ( 10 ): ): 3382 - - 3392 . . DOI: 10.7527/S1000-6893.2015.0093 http://doi.org/10.7527/S1000-6893.2015.0093 . .

C Jing , , , ZK Wang , , , L Fan , , , 等 . . Dynamics analysis of the constrained and centroid biased on-orbit satellite separation . . Flight Dynam , , 2010 . . 28 ( ( 1 ): ): 76 - - 79 . . DOI: 10.13645/j.cnki.f.d.2010.01.014 http://doi.org/10.13645/j.cnki.f.d.2010.01.014 . .

W Lan , , , J Brown , , , A Toorian , , , 等 . . CubeSat development in education and into industry . . AIAA SPACE Forum , , 2006 . . Article 7296 DOI: 10.2514/6.2006-7296 http://doi.org/10.2514/6.2006-7296 . .

JF Leng , , , X Gao , , , JP Zhu . . Application of multivariate linear regression statistical prediction model . . Stat Dec , , 2016 . . 7 82 - - 85 . . DOI: 10.13546/j.cnki.tjyjc.2016.07.021 http://doi.org/10.13546/j.cnki.tjyjc.2016.07.021 . .

JL Li , , , SZ Yan , , , XF Tan . . Modeling and simulation of clamp band dynamic envelope in a LV/SC separation system . . Appl Mech Mater , , 2012 . . 141 359 - - 363 . . DOI: 10.4028/www.scientific.net/AMM.141.359 http://doi.org/10.4028/www.scientific.net/AMM.141.359 . .

JL Li , , , SZ Yan , , , XF Tan . . Dynamic-envelope analysis of clamp-band joint considering pyroshock of satellite separation . . J Spacecr Rock , , 2014 . . 51 ( ( 5 ): ): 1390 - - 1400 . . DOI: 10.2514/1.A32382 http://doi.org/10.2514/1.A32382 . .

D Michaels , , , A Gany . . Modeling and testing of a tube-in-tube separation mechanism of bodies in space . . Acta Astronaut , , 2016 . . 129 214 - - 222 . . DOI: 10.1016/j.actaastro.2016.09.013 http://doi.org/10.1016/j.actaastro.2016.09.013 . .

K Miyamoto , , , K Ui , , , S Miyashita , , , 等 . . Tokyo tech separation demonstration TSD as M-V rocket sub-payload for nanosatellite separation mechanism . . 56 th Int Astronautical Congress of the Int Astronautical Federation, the Int Academy of Astronautics, and the Int Institute of Space LawArticle IAC-05-B5.6.A. , , 2005 . . DOI: 10.2514/6.IAC-05-B5.6.A.03 http://doi.org/10.2514/6.IAC-05-B5.6.A.03 . .

C Paris . . Vibration tests on the preloaded LARES satellite and separation system . . Aerosp Sci Technol , , 2015 . . 42 470 - - 476 . . DOI: 10.1016/j.ast.2015.01.023 http://doi.org/10.1016/j.ast.2015.01.023 . .

ZY Qin , , , SZ Yan , , , FL Chu . . Axial stiffness analysis of clamp band system . . J Astron , , 2009 . . 30 ( ( 5 ): ): 2080 - - 2085 . . DOI: 10.3873/j.issn.1000-1328.2009.05.056 http://doi.org/10.3873/j.issn.1000-1328.2009.05.056 . .

ZY Qin , , , SZ Yan , , , FL Chu . . Dynamic analysis of clamp band joint system subjected to axial vibration . . J Sound Vib , , 2010 . . 329 ( ( 21 ): ): 4486 - - 4500 . . DOI: 10.1016/j.jsv.2010.05.012 http://doi.org/10.1016/j.jsv.2010.05.012 . .

ZY Qin , , , SZ Yan , , , FL Chu . . Dynamic characteristics of launch vehicle and spacecraft connected by clamp band . . J Sound Vib , , 2011 . . 330 ( ( 10 ): ): 2161 - - 2173 . . DOI: 10.1016/j.jsv.2010.06.011 http://doi.org/10.1016/j.jsv.2010.06.011 . .

ZY Qin , , , SZ Yan , , , FL Chu . . Finite element analysis of the clamp band joint . . Appl Math Model , , 2012 . . 36 ( ( 1 ): ): 463 - - 477 . . DOI: 10.1016/j.apm.2011.07.022 http://doi.org/10.1016/j.apm.2011.07.022 . .

ZY Qin , , , SZ Yan , , , FL Chu . . Influence of clamp band joint on dynamic behavior of launching system in ascent flight . . J Aerosp Eng , , 2014 . . 228 ( ( 1 ): ): 97 - - 114 . . DOI: 10.1177/0954410012468070 http://doi.org/10.1177/0954410012468070 . .

J Singaravelu , , , D Jeyakumar , , , BN Rao . . Reliability and safety assessments of the satellite separation process of a typical launch vehicle . . J Def Model Simul: Appl Method Technol , , 2011 . . 9 ( ( 4 ): ): 369 - - 382 . . DOI: 10.1177/1548512911401939 http://doi.org/10.1177/1548512911401939 . .

S Somanath , , , Kutty VK Krishnan , , , EJ Francis , , , 等 . . Dynamics simulation of pyro actuated "ball lock" separation system for microsatellites to evaluate release shock . . 9 th European Space Mechanisms and Tribology Symp , , 2001 . . p.199 - - 206 . . . .

XF Tan , , , SZ Yan . . Dynamic simulation and failure analysis of a clamp band system for spacecraft . . J Tsinghua Univ (Sci Tech) , , 2010 . . 50 1205 - - 1209 . . DOI: 10.16511/j.cnki.qhdxxb.2010.08.012 http://doi.org/10.16511/j.cnki.qhdxxb.2010.08.012 . .

M Tayefi , , , M Ebrahimi . . Design and analysis of separation systems based on an optimization approach . . 47 th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition , , 2009 . . p.436 - - 445 . . DOI: 10.2514/6.2009-436 http://doi.org/10.2514/6.2009-436 . .

L Teng , , , ZH Jin . . Pico-satellite separation parameters optimization . . J Astronaut , , 2016 . . 37 ( ( 10 ): ): 1200 - - 1206 . . DOI: 10.3873/j.issn.1000-1328.2016.10.007 http://doi.org/10.3873/j.issn.1000-1328.2016.10.007 . .

QM Wang , , , XH Meng , , , QC Yang . . Research of simulation on programs of satellite secondary separation . . J Syst Simul , , 2010 . . 9 ( ( 22 ): ): 2217 - - 2222 . . DOI: 10.16182/j.cnki.joss.2010.09.010 http://doi.org/10.16182/j.cnki.joss.2010.09.010 . .

CJ Wu , , , XQ Xu . . New cage style pico-satellite deployer based on sliding guide structure . . J Zhejiang Univ (Eng Sci) , , 2014 . . 48 ( ( 3 ): ): 548 - - 554 . . DOI: 10.3785/j.issn.1008-973X.2014.03.025 http://doi.org/10.3785/j.issn.1008-973X.2014.03.025 . .

CJ Wu , , , XQ Xu , , , XE He , , , 等 . . A Novel Separation Mechanism Device for Controlling Pico-Satellite and Separation Method . . China Patent , , 2013 . . 201 210 573 701 . .

CX Xie , , , YT Xu , , , JZ Fu , , , 等 . . Kinematic system design of the pico-satellite separation mechanism . . J Astronaut , , 2014 . . 35 ( ( 6 ): ): 626 - - 632 . . DOI: 10.3873/j.issn.1000-1328.2014.06.002 http://doi.org/10.3873/j.issn.1000-1328.2014.06.002 . .

浏览量

Downloads

CSCD

文章被引用时，请邮件提醒。

Submit

工具集

关联资源

Visual interactive image clustering: a target-independent approach for configuration optimization in machine vision measurement