实现了对航天可展结构动力学性能在时频域内的“精细”考察，将有助于提高航天器结构的分析与设计水平。
The results provide precise measurements of the dynamics characteristics of the space deployable structure in the time-frequency domain, which are helpful for improving the system analysis and design.
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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