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首页> 外文期刊>Space technology >METHODOLOGY OF A THERMAL PROTECTION DESIGN FOR THE DESCENT MODULES INFLATABLE BRAKING DEVICE
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METHODOLOGY OF A THERMAL PROTECTION DESIGN FOR THE DESCENT MODULES INFLATABLE BRAKING DEVICE

机译：下降模块充气制动装置的热保护设计方法

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摘要

Space technology and the flexible heat-resistant materials currently developed enable the construction of inflatable descent module (DM). The front shield or its part for such DM is designed as an inflatable braking device (IBD), in the form of a closed, pressure-tight envelope taking a given shape after gas filling. During transportation, IBD is in stowed position and occupies a small volume on board the orbiter. Just before DM atmospheric entry, IBD is deployed in a working position. To save the IBD envelope during airbraking, it uses a flexible thermal protection system (TPS). In this paper, the logical order of action for TPS developing, methods, and technical means used at aerothermodynamic study of flexible TPS are described. This methodology has been developed TPS design and manufacturing of PENETRATOR probe for MARS-96 mission and DM DEMONSTRATOR used to study the possibility of inflatable reentry and descent technology (IRDT) application in space engineering. In this paper, the principle structure of multilayer flexible TPS and a list of materials recommended for its manufacture, the results of calculation of flexible TPS warm up, mass loss, and the results of experimental study of TPS samples efficiency are also described. The final test of TPS serviceability of the DM DEMONSTRATOR has been undertaken during full-scale DM mock-up testing in the wind tunnel at simultaneous reproduction of aerodynamic load upon DM and TPS thermal conditions. The results of these tests have also been given in this paper.
机译：当前开发的太空技术和柔性耐热材料使充气下降模块（DM）的构造成为可能。用于这种DM的前护板或其零件设计为可充气制动装置（IBD），其形式为密闭，不透气的外壳，在充气后呈给定形状。在运输过程中，IBD处于收起位置，并且在轨道飞行器上仅占很小的体积。在DM大气进入之前，IBD处于工作位置。为了在制动时保存IBD外壳，它使用了灵活的热保护系统（TPS）。本文介绍了柔性TPS的热力学研究中用于TPS开发的逻辑顺序，方法和技术手段。此方法已开发用于TPS设计和用于MARS-96任务的PENETRATOR探针和DM DEMONSTRATOR的制造，用于研究充气再入和下降技术（IRDT）在太空工程中的应用可能性。本文还介绍了多层柔性TPS的原理结构和推荐制造的材料清单，柔性TPS预热，质量损失的计算结果以及TPS样品效率的实验研究结果。 DM演示器的TPS可服务性的最终测试是在风道中进行完全DM实体模型测试时进行的，同时在DM和TPS热条件下同时再现了空气动力载荷。这些测试的结果也已在本文中给出。

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