基于烧蚀机理的涂层类防热结构精细化设计方法  

Refined Design Method of Coating Thermal Protection Structure based on Ablation Mechanism

作　　者：金玲[1] 张程[1,2] 卞亚东[1] 陈克 刘轩秀 JIN Ling;ZHANG Cheng;BIAN Yadong;CHEN Ke;LIU Xuanxiu(China Academy of Launch Vehicle Technology,Beijing,100076;College of Aerospace Science and Engineering,National University of Defense Technology,Changsha,410073)

机构地区：[1]中国运载火箭技术研究院,北京100076 [2]国防科学技术大学航天科学与工程学院,长沙410073

出　　处：《导弹与航天运载技术（中英文）》2024年第1期46-50,共5页Missiles and Space Vehicles

摘　　要：为了实现轻质化、低成本、精细化防热设计,提出基于烧蚀机理的涂层类防热结构精细化设计方法,使用烧蚀机理初步计算出涂层烧蚀碳层厚度,从而建立烧蚀精细化热仿真计算模型,并计算得到较为准确的防隔热仿真结果,该方法的应用可为舱段涂层防热方案论证提供科学有效的理论分析手段,指导防热方案设计,并达到降低设计成本、缩短研制周期的目的。In order to achieve lightweight,low cost and refined thermal design,the refined design method of coating thermal protection structure based on ablation mechanism is proposed.It can calculate the thickness of ablative carbon layer with using ablation mechanism,build thermal simulation model of ablation refinement and calculat accurate thermal simulation results.The application of this method can provide an effective and scientific theoretical analysis method for the demonstration of coating thermal protection scheme.It can guide the design of thermal protection scheme,reduce the design cost and shorten the development period.

关 键 词：烧蚀机理 涂层 防热结构 精细化 设计方法 

分 类 号：V414.8[航空宇航科学与技术—航空宇航推进理论与工程]