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高速飞行器对结构效率的苛刻要求使得热防护系统不断趋于向轻质化、集成化方向发展,新型的力热耦合一体化热防护系统(ITPS)极具发展潜力。首先阐释了一种新型一体化热防护方案的概念与特点,总结了一体化结构设计的基本原则,数值分析了结构参数对背面温度响应、屈曲临界载荷的影响,结果表明腹板厚度对背面温度以及屈曲临界载荷的影响最大。然后设计并加工制备了ITPS的面板与单胞试验样件,分别展开了800℃的高温防隔热性能试验考核和屈曲性能的力学试验研究;试验表明腹板结构是引发热短路效应和屈曲的关键因素,屈曲试验与模拟结果吻合,高温屈曲分析表明温度梯度对屈曲特征有较大影响。
Harsh requirements for structural efficiency of high-speed aircraft make the thermal protection system continue to tend towards light weight and integrated development. The new thermal integrated thermal protection system (ITPS) has great potential. First of all, the concept and characteristics of a new integrated thermal protection scheme are explained. The basic principles of integrated structural design are summarized. The influence of structural parameters on the back temperature response and buckling critical load is analyzed numerically. The results show that the influence of web thickness on backside temperature As well as the buckling critical load the greatest impact. Then, the ITPS panels and single cell test samples were designed and processed. The thermal insulation test of 800 ℃ and the mechanical test of buckling performance were carried out respectively. The experimental results show that the web structure is the cause of thermal short-circuit and buckling The key factors, buckling test and simulation results are in good agreement. The analysis of high temperature buckling shows that the temperature gradient has a great influence on the buckling characteristics.