复杂构型前缘疏导热防护技术  

Complex Dredging Thermal Protection Structure for Leading Edge

作　　者：艾邦成[1] 陈思员[1] 韩海涛[1] 胡龙飞[1] 初敏 曲伟[1] 俞继军[1] AI Bang-cheng;CHEN Si-yuan;HAN Hai-tao;HU Long-fei;CHU Min;QU Wei;YU Ji-jun(China Academy of Aerospace Aerodynamics , Beijing 100074 , China)

机构地区：[1]中国航天空气动力技术研究院,北京100074

出　　处：《气体物理》2019年第1期1-7,共7页Physics of Gases

基　　金：航天十一院自主创新研发项目:创新气动布局低成本飞行试验研究

摘　　要：针对前缘驻点区热流密度高、热流梯度大的特点,基于疏导式热防护思想,研制了一体化疏导式热防护前缘结构.根据力热承载要求,设计了一体化薄壁结构方案,内部充装碱金属工质,在气动加热条件下形成工质相变及输运的热管式闭式循环,实现驻点区热量的快速疏散.通过结构封装、热管充装等工艺流程,实现结构样件,最终通过了飞行试验验证.结果表明,疏导结构启动时间约为94.5 s,疏导效率达到23.4%.Based on dredging thermal protection method , an integrated leading edge structure was proposed to accommodate the severe heat flux and high heat flux gradient at the stagnation point. Considering the heat and force loadings , a thin shell structure with internal working medium was designed. Under thermal heating conditions , phase change and circulation of the working medium were established to achieve rapid heating transportation for the stagnation zone. The structure was integrated and then charged with working medium , and finally verified in flight test. The results showed that it started at about 94.5 s , and the thermal dredging efficiency achieved 23.4%.

关 键 词：疏导热防护 前缘 热管 启动 疏导效率 

分 类 号：V414.9[航空宇航科学与技术—航空宇航推进理论与工程]