针对在采用反馈线性化理论设计导弹飞行控制系统时控制器算法对导弹逆模型的要求 ,推导了导弹运动方程的逆解析解 ,包括导弹质心运动的运动学方程及其动力学方程的逆解析解、姿态运动的运动学方程及其动力学方程的逆解析解 ,详细给出了逆模型的求解过程 ,为一类飞行控制系统运用全局线性化设计奠定了基础。最后 ,结合工程应用进行了仿真计算 ,仿真结果表明逆解析解的推导是正确的 Aiming at the requirements of the controller algorithm for the missile inverse model when designing the missile flight control system using the feedback linearization theory, the inverse analytical solution of the missile’s motion equation is derived, including the kinematics equation of missile’s mass center motion and the inverse analytical solution of the dynamic equation , The kinematic equation of attitude movement and the inverse analytical solution of its kinetic equation, the solving process of inverse model is given in detail, which lays the foundation for a kind of flight control system using global linearization design. Finally, the simulation calculation is carried out based on the engineering application. The simulation results show that the derivation of inverse analytical solution is correct