建立了再入机动弹道数学模型，给出了气动力系数为速度、迎角、高度的函数拟合式，进行了最佳再入机动弹道设计和仿真计算。
The mathematical model of reentry maneuvering trajectory is established. The fitting expression of aerodynamic coefficient function on velocity, attack of Angle and altitude is presented.
实例计算结果表明，设计的下滑基准弹道可以满足载机不同发射速度、不同发射高度条件下弹道的技术要求。
The calculation result of example shows that glide standard trajectory designed can meet the trajectory tactical requirements when missile is launched in different velocity and altitude.
根据惯导、高度表和雷达提供的信息，设计了以弹道倾角为被控对象的导引规律，实现了以上目标。
Based on the information obtained from INS, altimeter and radar, the guidance law with trajectory inclination Angle as its controlled output is designed to achieve the above goal.
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