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.
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.
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