An economical and practical method is conducted for the study of nutation instability on a spinning solid-propellant rocket. The simulation is designed to match actual operation as closely as possible to obtain accurate data and help select an optimum spin rate of spinning solid propellant rockets of satellite orbit transfer system. The observation of full-scale rockets in flight shows that the nutation instability phenomena, which appear during motor burn causes the satellites to fall into over-control. This paper addresses the hot fire testing of subscale solid propellant rockets with HTPB/AT /AL propellant. A result of the study present the behavior of rocket motor causes particle accumulation and triggers the primary original of nutation instability by the low frequency disturbance on the side wall of the rocket motor.