设计了固体运载火箭上升段飞行程序，应用修正牛顿迭代法求解上升段弹道控制参数，推导了迭代算法公式。
We designed the flight program for solid launch vehicles, resolved the control parameter of ascent trajectory with modified Newton iterative method, and deduced the iterative formula.
亚声速气动力采用面源法计算，高超声速气动力采用修正的牛顿流理论计算。
Panel Method was used for subsonic aerodynamic analysis, and the Modified Newtonian Impact Theory was used for hypersonic aerodynamic analysis.
无论是采用牛顿·拉弗逊法还是其修正的方法，结果相差不多，特别是加载次数增多时，两者的计算数值趋于一致，所以其实质上是完全相同的。
The calculating results are almost equal whether Newton-Raphson method or its modified form is used, especially with more times of loading, which indicates that essential of the two methods is same.
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