Abstract
Separation velocity and angular velocity are two key factors affecting the success of space ejection separation. In this paper, a coupled dynamic model of micro-spacecraft ejection separation mechanism is built based on the Newton-Euler method. With this model as the research object, the influences of different system parameters on the separation velocity and the angular velocity of the ejection separation mechanism are simulated and analyzed. The results indicate that the physical parameters of separating springs and the installation position of space ejection separation mechanism are the main factors affecting the separation velocity and angular velocity respectively.
This is a preview of subscription content, log in via an institution to check access.
Access this chapter
Tax calculation will be finalised at checkout
Purchases are for personal use only
References
Woellert K, Ehrenfreund P, Ricco AJ, et al. Cubesats: cost-effective science and sechnology platforms for emerging and developing nations. Adv Space Res. 2011;47(3):663–84.
Gongbo W, Xiaoning X. Safe on-orbit releasing velocity design for small satellites. Chin Space Sci Technol. 2007;27(3):33–8.
Fuxiang X. Satellite engineering. Beijing: China Astronautic Publishing House; 2004.
Xingzhi H. Research on design, analysis, and optimization of separation systems for small satellites. National University of Defense Technology; 2012.
Zhigang W, Yanan Y, Yifan D. Dynamics analysis of the spatial catation problem. Flight Dyn. 2014;32(3):239–42.
Xingzhi H, et al. Dynamics and transient perturbation analysis of satellite separation systems. Proc Inst Mech Eng Part G J Aerosp Eng. 2012;227(12):1968–76.
Jiang C, Zhaokui W, Li F, Yulin Z. Dynamics analysis of the constrained and centroid biased on-orbit satellite separation. Flight Dyn. 2010;28(1):76–9.
Miyamoto K, Ui K, Miyashita N, et al. Tokyo tech separation demonstration TSD as M-V rocket sub-payload for nanosatellite separation mechanism. Int Conf Eng Geol New Millennium. 2005;179:2330–8.
Xiaonan H, Jun W, Jinsheng P, et al. Design and experimental research of a large load and low shock release device on shape memory alloy. Sci Technol Eng. 2016;16(30):319–23.
Wei H. Robot dynamics and control. Beijing: Higher Education Press; 2004.
Xingzhi H, Xiaoqian C, Yong Z. Coordinate transform methods used in dynamic simulation of satellite separation. Adv Mater Res. 2012;569:712–7.
Gongbo W, Xiaoning X. Safe onorbit releasing velocity design for small satellites. Chin Space Sci Technol. 2007;27(3):33–8.
Qingyang L. Numercial analysis. Beijing: Tsinghua Press; 2008.
Acknowledgements
This work was supported by the NSFC (61327807, 61521091, 61520106010, 61134005), the National Basic Research Program of China (973 Program: 2012CB821200, 2012CB821201) and the Fundamental Research Funds for the Central Universities (YMF-16-GJSYS-31, YMF-16-GJSYS-32).
Author information
Authors and Affiliations
Corresponding author
Editor information
Editors and Affiliations
Rights and permissions
Copyright information
© 2018 Springer Nature Singapore Pte Ltd.
About this paper
Cite this paper
Zhao, X., Jia, Y., Ling, J., Li, Y. (2018). Dynamic Modeling and Analysis of the Micro-spacecraft Ejection Separation System. In: Jia, Y., Du, J., Zhang, W. (eds) Proceedings of 2017 Chinese Intelligent Systems Conference. CISC 2017. Lecture Notes in Electrical Engineering, vol 459. Springer, Singapore. https://doi.org/10.1007/978-981-10-6496-8_23
Download citation
DOI: https://doi.org/10.1007/978-981-10-6496-8_23
Published:
Publisher Name: Springer, Singapore
Print ISBN: 978-981-10-6495-1
Online ISBN: 978-981-10-6496-8
eBook Packages: EngineeringEngineering (R0)