Journal of Astronautics ›› 2016, Vol. 37 ›› Issue (10): 1200-1206.doi: 10.3873/j.issn.1000-1328.2016.10.007

Previous Articles     Next Articles

Pico Satellite Separation Parameter Optimization

TENG Lai, JIN Zhong he   

  1. School of Aeronautics and Astronautics, Zhejiang University, Hangzhou 310027, China
  • Received:2016-02-25 Revised:2016-07-11 Online:2016-10-15 Published:2016-10-25

Abstract:

In order to achieve the non-interference separation of Zhejiang University’s Pico-Satellite 2, and the initial attitude of the satellite, a pico-satellite separation mechanism is designed, theoretically analyzed and optimized. By analyzing the dynamic characteristics of the separation system, the key factors affecting the separation system are obtained. Meanwhile, the satellite-rocket separation mechanism and motion system are optimized and verified through experiments. The simulation analysis and experimental results indicate that the design can meet the separation mechanism’s requirements on separation velocity and angular velocity, the simulated analysis and test verification of the satellite-rocket separation process indicate that the satellite-rocket separation mechanism of Zhejiang University’s Pico-Satellite 2 can achieve the non-interference separation, and the initial velocity and angular velocity of the Pico-Satellite can meet various requirements on the initial separation attitude.

Key words: Pico-satellite, Satellite-rocket separation mechanism, Kinematic analysis, Parameters optimization

CLC Number: