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中文摘要：
高超声速飞行器在出入大气层或持续在空间飞行时,将遭受严苛的气动加热载荷.对热防护系统进行传热分析是进行热力耦合分析的基础,而温度分布的特点直接影响到波纹夹芯结构的热应力等问题.首先对一体化热防护系统（integrated thermal protection system,ITPS）进行隔热性能分析,得到整个结构的温度场;然后采用顺序耦合的数值方法,模拟分析ITPS波纹夹芯结构单胞的热力耦合性能,给出波纹夹芯结构在静力载荷以及热力耦合载荷条件下的应力场、位移场,并对计算结果进行了讨论.结果表明波纹夹芯结构在初始尺寸及约束条件下,只满足在高温热流作用下飞行器低压区使用,而当气动压力大于等于15 000 Pa时,结构将发生破坏.
英文摘要：
Hypersonic aircrafts enter across the atmosphere with high flight speed and over a long period of time,resulting in an intense aerodynamic heating load.Thermal analysis of thermal protection system（TPS） is the base of thermal-mechanical coupling analysis;and the characteristics of temperature distribution affect thermal stress of corrugated sandwich structure directly.The analysis process was divided into three steps.The insulation performance of the integrated thermal protection system（ITPS） was analyzed to get the temperature distribution firstly.Then a sequence coupled numerical method was used to simulate the thermo-mechanical coupling performance of ITPS.Finally the stress field and displacement field of the corrugated sandwich structure unit cell were obtained and results were discussed.The calculation results show that the structure with initial size and constraints only satisfy the use of low-pressure zone,and structure will fail when the pressure is greater than 15 000 Pa.
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