The present model is capable of estimating aerodynamic coefficient ratios including the important static stability margin.
本模型可精确估计气动系数比，其中包括重要的静稳定度。
The aerodynamic coefficient varies with dynamic pressures always linearly, no matter what a rigid aerodynamic force may be linear or non-linear.
不论刚体气动力为线性还是非线性，气动力系数随动压变化的趋势均呈线性。
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.
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。
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