Full Text:   <908>

Summary:  <172>

CLC number: TH122

On-line Access: 2018-07-02

Received: 2017-06-24

Revision Accepted: 2017-08-29

Crosschecked: 2018-05-04

Cited: 0

Clicked: 1738

Citations:  Bibtex RefMan EndNote GB/T7714

 ORCID:

Lai Teng

http://orcid.org/0000-0002-0329-5302

-   Go to

Article info.
Open peer comments

Frontiers of Information Technology & Electronic Engineering  2018 Vol.19 No.5 P.685-698

http://doi.org/10.1631/FITEE.1700416


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


Author(s):  Lai Teng, Zhong-he Jin

Affiliation(s):  School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China

Corresponding email(s):   tenglai@zju.edu.cn

Key Words:  Pico-satellite, Satellite–rocket separation mechanism, Separation parameters, Parameter optimization


Share this article to: More <<< Previous Article|

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.

@article{title="A composite optimization method for separation parameters of large-eccentricity pico-satellites",
author="Lai Teng, Zhong-he Jin",
journal="Frontiers of Information Technology & Electronic Engineering",
volume="19",
number="5",
pages="685-698",
year="2018",
publisher="Zhejiang University Press & Springer",
doi="10.1631/FITEE.1700416"
}

%0 Journal Article
%T A composite optimization method for separation parameters of large-eccentricity pico-satellites
%A Lai Teng
%A Zhong-he Jin
%J Frontiers of Information Technology & Electronic Engineering
%V 19
%N 5
%P 685-698
%@ 2095-9184
%D 2018
%I Zhejiang University Press & Springer
%DOI 10.1631/FITEE.1700416

TY - JOUR
T1 - A composite optimization method for separation parameters of large-eccentricity pico-satellites
A1 - Lai Teng
A1 - Zhong-he Jin
J0 - Frontiers of Information Technology & Electronic Engineering
VL - 19
IS - 5
SP - 685
EP - 698
%@ 2095-9184
Y1 - 2018
PB - Zhejiang University Press & Springer
ER -
DOI - 10.1631/FITEE.1700416


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.

一种大偏心皮卫星分离参数复合优化方法

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。

关键词:皮卫星;星箭分离机构;分离参数;参数优化

Darkslateblue:Affiliate; Royal Blue:Author; Turquoise:Article

Reference

[1]Chao J, Wang ZK, Zhang YL, 2015. Development of the new approach of formation initialization using spring separation mechanism considering J2 perturbation. Adv Space Res, 55(11):2616-2627.

[2]Cui DL, Yan SZ, Li JL, et al., 2014. Dynamic analysis of satellite separation considering the flexibility of interface rings. J Aerosp Eng, 229(10):1886-1902.

[3]Cui DL, Zhao JL, Yan SZ, et al., 2015. Analysis of parameter sensitivity on dynamics of satellite separation. Acta Astronaut, 114(3):22-33.

[4]Fritz M, Berger PD, 2015. 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, p.239-269.

[5]Hu J, Li HC, Zhou YP, 2012. The application of Levenberg-Marquardt algorithm in the image stitching. Telecom Mark, 2:149-154 (in Chinese).

[6]Hu XZ, Chen XQ, Tuo ZH, et al., 2013. Dynamics and transient perturbation analysis of satellite separation systems. Proc Inst Mech Eng G, 227(12):1968-1976.

[7]Hu XZ, Chen XQ, Zhao Y, et al., 2014a. Optimization design of satellite separation systems based on multi-island genetic algorithm. Adv Spac Res, 53(5):870-876.

[8]Hu XZ, Chen XQ, Tuo ZH, et al., 2014b. Simplified metrics of elastic potential energy for spacecraft separation dynamics. Acta Astronaut, 102:151-155.

[9]Hu XZ, Chen XQ, Zhao Y, et al., 2017. Active subspace approach to reliability and safety assessments of small satellite separation. Acta Astronaut, 131:159-165.

[10]Huang WH, Cao DQ, Han ZY, 2012. Advances and trends in dynamics and control of spacecrafts. Adv Mech, 42(4): 367-394.

[11]Iwasa T, Shi Q, Ando S, et al., 2007. Simplified SRS prediction method for pyroshock source of V-band clamp separation devices. 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conf, p.1-12.

[12]Jiang C, Wang ZK, Zhang YL, 2015. Angular velocity depressing method of constrained and centroid biased on-orbit separation. Acta Aeronaut Astronaut Sin, 36(10): 3382-3392 (in Chinese).

[13]Jing C, Wang ZK, Fan L, et al., 2010. Dynamics analysis of the constrained and centroid biased on-orbit satellite separation. Flight Dynam, 28(1):76-79 (in Chinese).

[14]Lan W, Brown J, Toorian A, et al., 2006. CubeSat development in education and into industry. AIAA SPACE Forum, Article 7296.

[15]Leng JF, Gao X, Zhu JP, 2016. Application of multivariate linear regression statistical prediction model. Stat Dec, 7:82-85 (in Chinese).

[16]Li JL, Yan SZ, Tan XF, 2012. Modeling and simulation of clamp band dynamic envelope in a LV/SC separation system. Appl Mech Mater, 141:359-363.

[17]Li JL, Yan SZ, Tan XF, 2014. Dynamic-envelope analysis of clamp-band joint considering pyroshock of satellite separation. J Spacecr Rock, 51(5):1390-1400.

[18]Michaels D, Gany A, 2016. Modeling and testing of a tube-in-tube separation mechanism of bodies in space. Acta Astronaut, 129:214-222.

[19]Miyamoto K, Ui K, Miyashita S, et al., 2005. Tokyo tech separation demonstration TSD as M-V rocket sub-payload for nanosatellite separation mechanism. 56th Int Astronautical Congress of the Int Astronautical Federation, the Int Academy of Astronautics, and the Int Institute of Space Law, Article IAC-05-B5.6.A.

[20]Paris C, 2015. Vibration tests on the preloaded LARES satellite and separation system. Aerosp Sci Technol, 42: 470-476.

[21]Qin ZY, Yan SZ, Chu FL, 2009. Axial stiffness analysis of clamp band system. J Astron, 30(5):2080-2085 (in Chinese).

[22]Qin ZY, Yan SZ, Chu FL, 2010. Dynamic analysis of clamp band joint system subjected to axial vibration. J Sound Vib, 329(21):4486-4500

[23]Qin ZY, Yan SZ, Chu FL, 2011. Dynamic characteristics of launch vehicle and spacecraft connected by clamp band. J Sound Vib, 330(10):2161-2173.

[24]Qin ZY, Yan SZ, Chu FL, 2012. Finite element analysis of the clamp band joint. Appl Math Model, 36(1):463-477.

[25]Qin ZY, Yan SZ, Chu FL, 2014. Influence of clamp band joint on dynamic behavior of launching system in ascent flight. J Aerosp Eng, 228(1):97-114.

[26]Singaravelu J, Jeyakumar D, Rao BN, 2011. Reliability and safety assessments of the satellite separation process of a typical launch vehicle. J Def Model Simul: Appl Method Technol, 9(4):369-382.

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

[28]Tan XF, Yan SZ, 2010. Dynamic simulation and failure analysis of a clamp band system for spacecraft. J Tsinghua Univ (Sci Tech), 50:1205-1209 (in Chinese).

[29]Tayefi M, Ebrahimi M, 2009. Design and analysis of separation systems based on an optimization approach. 47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, p.436-445.

[30]Teng L, Jin ZH, 2016. Pico-satellite separation parameters optimization. J Astronaut, 37(10):1200-1206 (in Chinese).

[31]Wang QM, Meng XH, Yang QC, 2010. Research of simulation on programs of satellite secondary separation. J Syst Simul, 9(22):2217-2222 (in Chinese).

[32]Wu CJ, Xu XQ, 2014. New cage style pico-satellite deployer based on sliding guide structure. J Zhejiang Univ (Eng Sci), 48(3):548-554 (in Chinese).

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

[34]Xie CX, Xu YT, Fu JZ, et al., 2014. Kinematic system design of the pico-satellite separation mechanism. J Astronaut, 35(6):626-632.

Open peer comments: Debate/Discuss/Question/Opinion

<1>

Please provide your name, email address and a comment





Journal of Zhejiang University-SCIENCE, 38 Zheda Road, Hangzhou 310027, China
Tel: +86-571-87952783; E-mail: cjzhang@zju.edu.cn
Copyright © 2000 - Journal of Zhejiang University-SCIENCE