应用双时标的假设 ,将导弹动力学分离为快变状态动力学和慢变状态动力学。然后 ,对慢变动力学和快变动力学分别进行反馈线性化设计。考虑到空气动力系数具有较大的不确定性 ,进一步 ,对期望的慢变动力学和快变动力学进行鲁棒控制设计。 6DOF数学仿真验证了该方法的有效性 Under the assumption of double time-scale, missile dynamics are separated into fast-changing state dynamics and slowly-changing state-dynamics. Then, the slow-change dynamics and fast-change dynamics were respectively linearized by feedback design. Considering the great uncertainty of the aerodynamic coefficient, further, the robust control design of the desired slow-change dynamics and fast-change dynamics is carried out. The 6DOF mathematical simulation verifies the effectiveness of this method