Design of the spontaneous deployable mechanism for space telescope based on lenticular tape springs

被引：0
|
作者：
Zuo Y. [1 ,2 ]
Jin G. [1 ,2 ]
Xie X. [1 ]
Li Z. [1 ]
Xie P. [1 ]
机构：
[1] Changchun Institute of Optics, Fine Mechanics and Physics, Chinese Academy of Sciences, Changchun
[2] University of Chinese Academy of Sciences, Beijing
来源：
| 1600年 / Chinese Society of Astronautics卷 / 46期
关键词：
Deployment mechanism; Lenticular tape spring; Microsatellite; Optical system; Space telescope;
D O I：
10.3788/IRLA201746.0518002
中图分类号：
学科分类号：
摘要：
In order to reduce launch mass and volume of the space telescope apparently, and to make it suitable for the vehicle requirements of the microsatellite, a new spontaneous deployment mechanism of the space telescope based on the lenticular tape springs was designed, which aimed at one optical system. Firstly, the geometrical sizes of the lenticular tape spring used in this article were preliminarily designated through theoretical analysis, and a new spontaneous deployment mechanism based on the lenticular tape springs was designed aimed at one space optical system. Secondly, the finite element model of the deployment mechanism was built, and its deployment characters were analyzed. Finally, the prototype of the spontaneous deployment mechanism was built up and the experiment was carried out to study its characters. Experimental results indicate that the deployment mechanism is 500 mm in height when it has deployed, and the repetitive deploy accuracy of it can be reached much less than 0.1 mm, also, the fundamental frequency is about 35.5 Hz when it has deployed. It can satisfy the deployment mechanism's requirements of simple structure, low mass, steady and reliable deployment, as well as higher precision for space telescope. © 2017, Editorial Board of Journal of Infrared and Laser Engineering. All right reserved.
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共 17 条
  • [1] Xu F., Introduction of Satellite Engineering, (2003)
  • [2] Zheng Y., Ruan P., Cao S., Deployable structure design and analysis for space membrane diffractive telescope, Infrared and Laser Engineering, 45, 1, (2016)
  • [3] Seffen K.A., Pellegrino S., Deployment dynamics of tape springs, Proceedings of the Royal Society of London, 455, pp. 1003-1048, (1999)
  • [4] Boone B.G., Bruzzi J.R., Kluga B.E., Et al., Development and testing of an actively-controlled large aperture Cassegrain telescope for spacecraft deployment, 5487, pp. 1042-1053, (2004)
  • [5] Black J.T., Whetzal J.A., Deblonk B.J., Et al., Deployment repeatability testing of composite tape springs for space optics applications, Collection of Technical Papers-AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, (2006)
  • [6] Aridon G., Almajid A., Demond D., Et al., A Self-deployment hexapod model for a space application, Journal of Computational and Nonlinear Dynamics, 4, 1, pp. 651-658, (2009)
  • [7] Zhao C., Li C., Zhou N., A deployable telescope imaging system with coilable tensegrity structure for microsatellite application, 8908, 2, pp. 165-189, (2013)
  • [8] Soykasap O., Analysis of tape spring hinges, International Journal of Mechanical Sciences, 49, pp. 853-860, (2007)
  • [9] Wuest W., Einige anwendungen der theorie der zylinderschale, Zeitschrift fur Angewandte Mathematik and Mechanik, 34, pp. 444-454, (1954)
  • [10] Guo P., Zhang J., Yang F., Et al., Design and buckling analysis of TMT tertiary mirror cell assembly flexure structure, Infrared and Laser Engineering, 44, 12, pp. 3650-3655, (2015)
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