Study on influence of initial deviation on motion attitude of spacecraft

Deployable spacecraft have been widely used, while the motion state under the disturbance is still unknown. A test device is designed to simulate the motion of deployable spacecraft in this paper, and the ballistic characteristics of solid thruster are tested. The test results show that the total impulse deviation of the solid thruster can be effectively reduced by controlling the propellant mass, but the spacecraft would still produce a large precession angle and precession angular rate. The influence of launch disturbance and deployment disturbance on the spacecraft is larger than that of spinning thruster deviation. The ratio between the transverse moment of inertia and the axial moment of inertia should be increased as much as possible during the design of the spacecraft, otherwise a small disturbance would produce a large precession angle. The test results have certain reference significance for the study of the spacecraft micro-motion.