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典型部件疏导式热防护试验技术研究
Investigation on Testing Technology of Typical Component Dredging Thermal Protection
投稿时间:2018-08-14  修订日期:2018-12-08
DOI:
中文关键词:  疏导式热防护  烧蚀  试验条件  防热层  热流
英文关键词:dredging thermal protection  ablation  test conditions  heat protection layer  heat flux
基金项目:
作者单位E-mail
朱晓军 中国航天空气动力技术研究院 zxj011010826@163.com 
李锋 中国航天空气动力技术研究院  
欧东斌 中国航天空气动力技术研究院  
陈连忠 中国航天空气动力技术研究院  
周凯 中国航天空气动力技术研究院  
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中文摘要:
      疏导式热防护是一种新概念非烧蚀热防护技术,对未来高超声速飞行器发展具有十分重要的意义。为了验证疏导式热防护原理的有效性、合理性和优越性,并考核疏导式热防护技术实现途径的可行性,在传统热防护试验模拟技术、试验与测试的基础上,建立了疏导式热防护试验条件和试验的做法,并考核了高温热管球柱疏导模型的疏导效果。结果表明:对于高温热管球柱疏导模型在防热层装入快速导热元件后可以有效地降低驻点高热流区的表面温度,提升低温区的表面温度,从而降低整体温差基本实现非烧蚀。可以得出该试验技术能够满足典型部件疏导式热防护机理探索及性能考核研究。
英文摘要:
      Dredging thermal protection is a new concept of non-ablative thermal protection, which is of great significance to the future development of hypersonic vehicle. In order to verify the validity, rationality and superiority of the dredging thermal protection principle and to assess the feasibility of the diversion thermal protection technology. On the basis of the traditional simulation technology and testing technology of thermal protection test, the experimental conditions and test methods of dredging thermal protection are established, the dredging effect of High temperature heat pipe sphere column dredging model is examined. The results show that: after rapid thermal conduction element is installed into the the heat-resistant inner layer, the surface temperature of the stagnation point high heat flow area can be effectively reduced, the surface temperature of the low-temperature region of the cylinder surface can be increased, so the overall temperature difference is reduced to basically achieve non ablation.It can be concluded that the test technology can meet the exploration of typical component dredging thermal protection mechanism and the research of performance evaluation.
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