عنوان مقاله [English]
نویسندگان [English]چکیده [English]
This paper presents the new method for separation of satellite from launch vehicle. In this method, in addition to helical compression spring mechanism used in usual separation systems, two brake engines mounted symmetrically on the second stage were used. To protect on-going stage from disturbance, brake engine performance was initiated a few millisecond after satellite separation. Linear and rotational equations were solved by 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 satellite separating from spent body.