Journal of Astronautics ›› 2014, Vol. 35 ›› Issue (6): 626-632.doi: 10.3873/j.issn.1000-1328.2014.06.002

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Kinematic System Design of the Pico Satellite Separation Mechanism

XIE Chang xiong,  XU Yue tong,  FU Jian zhong,  WU Chang ju,  CHEN Zi chen   

  1. 1.Department of Mechanical Engineering, Zhejiang University, Hangzhou 310027, China;
    2.College of Mechanical Engineering, Quzhou University, Quzhou 324000, China;
    3.School of Aeronautics and Astronautics, Zhejiang university, Hangzhou 310027, China
  • Received:2013-04-26 Revised:2013-07-18 Online:2014-06-15 Published:2014-06-25


In order to realize the interference free separation of the ‘ZDPS 1A’ satellite from the rocket, and to meet the demand of initial attitude of separation, a novel pico satellite separation mechanism kinematic system is designed and developed. Firstly, according to the force between the satellite and the cam mechanism and energy conservation principle, the size of the cam contour and structure parameters of the separation spring are designed. And then, on the basis of above results, the dynamics model of separation process is established. Finally, through numerical calculation of the dynamics model, elasticity coefficient of the torsional spring is determined to meet the requirement of non interference separation. Simulation results and verification experiments show that the ‘ZDPS 1A’ satellite can separate successfully form the rocket without any interference. Furthermore, the initial velocity and angular rates of the satellite completely satisfies designed technical indexes.

Key words: Pico satellite, Satellite separation mechanism, Anti interference, Kinematic analysis

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