Abstract:

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