| Issue |
MATEC Web Conf.
Volume 108, 2017
2017 International Conference on Mechanical, Aeronautical and Automotive Engineering (ICMAA 2017)
|
|
|---|---|---|
| Article Number | 04009 | |
| Number of page(s) | 6 | |
| Section | Mechanical Engineering | |
| DOI | https://doi.org/10.1051/matecconf/201710804009 | |
| Published online | 31 May 2017 | |
Investigation on the design and the stiffness demonstration for a space square-truss deployable mast (STDM)
1 Aerospace System Engineering Shanghai, Shanghai, 3888 Yuanjiang Road, China
2 The State Key Laboratory of Mechanical Transmissions, Chongqing University, Chongqing, 174 Shazheng Road, China
Space deployable mast is an important device or system, which can deploy and support spacecraft fittings on orbit, such as payload, solar array, antenna, and etc. In order to achieve the pre-function of spacecraft fittings and attitude control of spacecraft, space deployable mast of high stiffness is required. Therefore, it is necessary to analyze the stiffness of the mast to ensure the capability. STDM consisting of longerons, rigid frames, flex-battens, hinge joints, and etc has higher stiffness than coil or articulated deployable mast. The design of STDM is presented, under the demand of future large-scale spacecraft. The theory analysis of stiffness is achieved and the impact factor are found, which establish the theoretical baseline for the optimization design and application of the mechanism product.
© The Authors, published by EDP Sciences, 2017
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