充气式再入航天器结构参数优化及防热试验工程方法

Design Optimization of Inflatable Reentry Vehicle Structure and Thermal Testing Engineering Method

用工程算法对充气式再入航天器的全展开半径,半锥角,刚性头锥半径与全展开半径之比三个方面的参数进行了优化计算,获得同时满足航天器质量,刚性头锥及柔性防热系统温度约束条件的充气式再入航天器的设计方案,计算得到了优化设计方案整个再入过程的外热流密度和温度变化规律,并且通过与文献中数据对比,验证了文中工程算法的正确性。针对再入过程的外热流密度和温度条件,参考充气式再入返回试验(Inflatable Reentry Vehicle Experiment,IRVE)典型防热材料,设计不同的柔性防热系统结构试验件。最后,通过热冲击试验,得到了各试验件冷端的温度响应,验证了各试验件在再入温度条件下防热性能。文章提出的柔性防热系统结构的改进方向,可为充气式再入航天器的设计分析提供参考。

This paper presents a detailed optimization of full deployed radius, half cone angle, the ratio of rigid nose cone radius to full deployed radius by engineering algorithm, and some inflatable reentry spacecraft design schemes that satisfying both mass and temperature constraints are obtained. In this paper, the heat flow and temperature variation of the entire reentry process of these optimization schemes are calculated. And through the comparison with the data in the reference, the correctness of the engineering algorithm in the paper is verified. According to the calculated heat conditions of the reentry process, different flexible thermal protection system structural test samples are designed refer to the typical thermal protection forms of IRVE in the reference. Finally, the thermal response of each test samples was obtained by thermal shock test, and the thermal insulation performance of each flexible thermal protection system was verified. This paper can provide some reference for the design and improvement direction of flexible thermal protection in inflatable reentry vehicle.