临近空间飞行器防隔热/承载一体化热结构设计及力/热行为

目的满足临近空间飞行器对结构/热防护系统质量指标的苛刻要求,研制兼具轻量化与高效防隔热/承载一体化的热防护结构及系统。方法根据临近空间飞行器承力和防热两方面的要求,设计一种全复合材料防隔热/承载一体化热防护结构,采用地面高温环境试验,考查复合材料一体化热防护结构的抗烧蚀性能。建立一体化热防护结构的热响应和力学响应预报方法,以某飞行器机翼为研究对象,开展一体化热防护结构在机翼部位的应用研究,利用有限元方法进行热力耦合分析。结果一体化热防护结构高温热暴露后表面出现热解,但结构性能保持良好。结论设计的一体化热防护结构满足防热和承载两方面设计要求,是新一代飞行器的理想热防护方案。

Design and Thermomechanical Behavior of Full-composite Structurally Integrated Thermal Protection Structure for Near Space Vehicles

The paper aims to develop a lightweight thermal protection structure and system with integrated thermal protection and load carrying capacities to meet the rigor requirement on structure and thermal protection system of near space vehicles. A full-composite structurally integrated thermal protection system (SITPS) was designed according to the requirements of both load carrying and heat resistant. The ablation properties of composite SITPS were studied by the thermal exposure experimental tests. Ablation and thermal protection mechanism of surface materials were studied. The modeling of thermal and mechanical responses of the SITPS was proposed. The application research of SITPS for the wings of a hypersonic vehicle was carried out. The coupled thermal and mechanical analysis was conducted through the finite element methods. Although the thermal decomposition existed on the heated surface of SITPS after thermal exposure test, the structural properties of the post-test SITPS was still good. The SITPS designed meets the design requirements of both thermal protection and load carrying, and is an ideal thermal protection scheme for the next generation of aerospace vehicles.