In order to solve the problem of deflection of missile’s center of mass, which is caused by missile assembly error, the influence of missile body closed-loop stability loop is analyzed. According to the dynamics equation of the projectile body, the open loop transfer function description model of the projectile body is established, and the stability loop of the projectile body is designed by using the angular rate feedback structure and the three-loop overload feedback structure independently. The robustness of the two closed-loop control structures is analyzed for a specific design example. The simulation results show that the three-loop overload feedback structure is more robust and the dynamic characteristics change little when the position of the missile’s center is shifted by 5%.