Journal of Astronautics ›› 2019, Vol. 40 ›› Issue (12): 1403-1411.doi: 10.3873/j.issn.1000-1328.2019.12.003

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Dynamic Simulation and Sensitivity Analysis of Picosatellite Separation System

XIE Chang xiong, DENG Xiao lei, WANG Jian chen, LIN Huan   

  1. 1. College of Mechanical Engineering, Quzhou University, Quzhou 324000, China; 2. Faculty of Mechanical Engineering & Automation, Zhejiang Sci Tech University, Hangzhou 310018, China;
    3. School of Mechanical Engineering, Zhejiang University, Hangzhou 310027, China
  • Received:2019-03-01 Revised:2019-06-10 Online:2019-12-15 Published:2019-12-25

Abstract: The picosatellite attitude control system makes high claims on orbit injection initial attitude for its limited energy and poor attitude control ability. In this article, based on the self-developed separation mechanism of picosatellite and the multi-body dynamics theory, the virtual prototype model of picosatellite and its separation mechanism is established by ADAMS software. The influences of the picosatellite eccentricity, the main spring elastic coefficient and the elastic coefficient of the torsional spring on the initial attitude are analyzed. The result shows that the eccentricity of the picosatellite has the most obvious influence on the separation attitude, followed by the elastic coefficient of the main spring and the torsional spring. The reasonable configuration of the elastic coefficient of the main spring and elastic coefficient of the torsional spring are conducive to maintain a good separation attitude. Moreover, the on-orbit separation test shows that the rolling rate, pitch rate and yaw rate are -0.18(°)/s,-1.60(°)/s and 0.95(°)/s respectively, which are consistent with the simulation results under the in-orbit environment. The initial attitude in orbit can satisfy the requirement of the attitude control system of picosatellite and provide guarantee for its follow-up activities.

Key words: Picosatellite, Satellite separation, Dynamics, Separation attitude, Sensitivity analysis

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