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科技导报  2015 

高超声速飞行器热防护系统分析与数值计算

DOI: 10.3981/j.issn.1000-7857.2015.05.010, PP. 66-71

Keywords: 高超声速飞行器,热防护系统,有限元

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Abstract:

针对大气环境内吸气式高超声速飞行器热防护要求,得出前缘、下表面和上表面的热防护结构应分别采用碳/碳(C/C)防热材料、刚性陶瓷防热瓦材料和柔性隔热毡材料。基于Abaqus分析软件建立以机身为主的热分析有限元模型,计算了高超声速飞行器在典型气动加热载荷情况下的温度场分布和在整个飞行过程中温度的变化情况。通过温度分布得到机身前缘的峰值温度达1637℃,上下表面峰值温度分别为635、805℃,验证了本研究提出的热防护结构形式的有效性。通过温度与时间曲线得出飞行500s左右时,飞行器前缘及上下表面温度急剧增加、温度梯度大,500~1500s期间持续高温,在1500s后温度迅速降低。同时建立了C/C、陶瓷瓦及柔性隔热毡3种典型耐高温材料的传热模型,对其防热结构的防热效率进行评估,得到其最佳的防热材料厚度为57.6、52.9、53.3mm,可为防热结构的设计提供参考。

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