飞行器制导精度评估，特别是航天器的姿态与定点控制、落点预报等，都离不开高精度的外弹道测量数据。

Assessing the accuracy of guidance system, especially controlling of missile's attitude and station keeping maneuver and landing point forecasting all rely on the reliable trajectory measurement.

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介绍弹道式再入航天器烧蚀防热结构设计，文中说明了方案、材料选择、设计和分析计算。

This paper introduces ablative thermal protection structure design of a return module of some satellites.

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