DYNAMIC ANALYSIS OF SATELLITE SEPARATION USING RETRO ROCKET FOR INJECTION WITH INITIAL ROTATION IN ORBIT

This paper presents the new method for separation of payload from launch vehicle. In this method، in addition to helical compression spring mechanism used in usual separation systems، two retro rockets mounted symmetrically on the second stage were used. To protect on-going stage from disturbance، the retro rocket performance was initiated a few millisecond after payload separation. Linear and rotational equations were solved using MATLAB and the numerical analysis was done by ADAMS. The comparison among analytic، numeric and test results showed that this method could be used as an appropriate tool for payload separating from spent body.