摘要
烧蚀型热防护是高超声速飞行器应用最广泛的一种热防护形式,高温烧蚀理论及相关计算分析方法尚不完善,无法通过计算给出精确的烧蚀热防护系统的热流和温度时序。全方程热流密度控制试验模拟结构的真实飞行历程,计及气动加热与结构热响应的耦合效应并实时测量迭代,成为烧蚀型热防护系统性能测试和研究的重要措施。本文以典型舱段为试验研究对象,进行了全方程热流密度控制加热烧蚀试验,验证了全方程控制加热试验的可行性,提出了试验技术保障要求及未来仍需解决的技术难点。
Ablation thermal protection is the most widely used thermal protection form of hypersonic vehicle.The theory of high temperature ablation and related calculation and analysis methods are not perfect.It is impossible to calculate the heat flux and temperature sequence of ablation thermal protection system accurately.Considering the coupling effect of aerodynamic heating and structural thermal response and real-time measurement iteration,full equation heat flux control test can simulate the real flight history of the structure,and become an important measurement for the performance test and research of ablation thermal protection system.In this paper,the typical cabin is taken as the object of experimental research,and the full equation heat flux controlled heating ablation experiment is carried out.The feasibility of full equation controlled heating test is verified,and the test precautions and the technical difficulties to be solved in the future are put forward.
作者
付志鹏
陈宏
秦强
丛琳华
魏广平
Fu Zhipeng;Chen Hong;Qin Qiang;Cong Linhua;Wei Guangping(Aircraft Strength Research Institute of China,Xi′an 710065,Shaanxi,China)
出处
《工程与试验》
2021年第1期19-21,90,共4页
Engineering and Test
关键词
全方程控制方法
加热试验
烧蚀
full equation control method
heating experiment
ablation
