航天器工程2019，Vol.28Issue(2)：43-50,8.DOI:10.3969/j.issn.1673G8748.2019.02.007
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
摘要
Abstract
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 inflataG ble 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 referG ence,the correctness of the engineering algorithm in the paper is verified.According to the calcuG lated 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 therG mal protection in inflatable reentry vehicle.关键词
充气式再入/工程算法/柔性防热系统Key words
inflatable reentry/engineering algorithm/thermal protection system分类
航空航天引用本文复制引用
黄明星,曹旭,唐明章..充气式再入航天器结构参数优化及防热试验工程方法[J].航天器工程,2019,28(2):43-50,8.
