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1·Programming maneuvering flight guidance scheme about reentry vehicle is presented in this paper.

文提出一种关于再入飞行器程序机动飞行的制导方案。

2·An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.

研究了在降弧段进行高空机动的再入飞行器最优制导律。

3·High temperature chemical non equilibrium phenomena have a great effect on the flow field around a reentry vehicle.

高温非平衡化学反应对高超声速再入飞行器绕流流场的气动热特性有较大影响。

4·In this paper, plasma wake flow of hypersonic reentry vehicle and radar scattering characteristics have been studied.

对再入飞行器等离子体尾迹及其雷达散射特性进行了分析、研究和大量的计算。

5·Therefore, the direct collocation method is a viable approach to the reentry vehicle trajectory optimization problem.

因此，直接配点法对于再入轨迹优化问题的求解是可行的。

6·A novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.

针对高超声速再入飞行器最远距离滑翔制导关键技术，设计了一种新型制导律。

7·This paper gives the method that is effective in decreasing the roll Angle and roll rate in roll channel of the reentry vehicle.

针对再入飞行器滚动通道产生较大的滚动角及滚动角速率，给出了一种能够有效地减小滚动角和滚动角速率的方法。

8·A predictive guidance method for reentry vehicle in the case of attacking the stationary target on the surface is also investigated.

论文最后研究了预测制导方法在高速再入飞行器攻击地面固定目标任务中的应用问题。

9·This paper researches into reentry vehicle impact errors which result from the roll velocity changes by use of rotor dynamic theory.

用转子动力学理论研究了再入航天器滚速变化引起的落点误差。

10·This paper deals with the problem of determining the aerodynamic shape of a reentry vehicle with minimum total trajectory heat transfer.

本文研究确定再入飞行器的最小总加热量气动外形问题。