仿真表明，采用改进的显式制导，发动机工作时间有所增加，但邻近关机时推力方向平稳。
Simulations show that using the improved explicit guidance, the working time of the engine is increased while the direction of the thrust near shutoff keeps stable.
给出了一种新的飞行器运动数学模型和这一模型下的最优制导律以及再入飞行器发动机工作时间、过载系数和估算方法。
The optimal high altitude guidance law with reentry constraint condition is derived by using the optimal control theory, and the algorithm of time to go is also given.
发动机工作性能对火箭飞行性能的严重影响已引起众多研究人员的重视，尤其是火箭发动机推力总冲及其工作时间等重要参数。
The severe influence of the rocket engine property, especially its total thrust impulse and work time on the rocket flight performance has aroused great attention among technological workers.
旋转和不旋转情况下的计算结果对比表明，旋转使发动机内压强增高，工作时间缩短，拖尾段加长。
Computation shows that the spinning of SRM makes the pressure in combustion chamber high, action time short and the pressure descending stage long.
旋转和不旋转情况下的计算结果对比表明，旋转使发动机内压强增高，工作时间缩短，拖尾段加长。
Computation shows that the spinning of SRM makes the pressure in combustion chamber high, action time short and the pressure descending stage long.
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