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A New Device and Method for Simulating Hypersonic Aerothermal Environment

机译:一种模拟高超声气空气环境的新装置和方法

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When flying at hypersonic speed, aircraft will face severe aerodynamic heating. Its surface material must go through the aerothermal ablation test which is close to the actual fight before it can be used. The key of the test is to create an equivalent aerothermal environment on the ground. At present, the main methods used to simulate the aerothermal environment are quartz lamp heating, oxyacetylene premixed flame ablation, engine exhaust and high enthalpy wind tunnel. The high enthalpy wind tunnel can establish the aerothermal environment closest to the actual state, but the experimental cost is too high, and some parameters cannot meet the conditions. In this paper, the test simulation methods of aerothermal environment are summarized, and a more accurate similarity criteria of test parameters is proposed through the analysis of experimental parameters. In the criteria, when it is difficult to guarantee the same recovery enthalpy and cold-wall heat flow at the same time, it is necessary to take the equal hot-wall heat flux as the basic principle, and then the recovery temperature of test gas should be adjusted according to the convective heat transfer coefficient under ground test conditions, so as to meet the test requirements. This paper also designs a new type of aerothermal environment simulation device, which has the characteristics of simpler operation, lower cost and simpler parameter adjustment. Material ablation experiments in hypersonic fight environment were carried out using the method and equipment proposed in this paper. The experimental results are close to those of arc wind tunnel test. This shows that the proposed test device and parameter similarity method can not only simulate the high temperature aerothermal environment, but also broaden the parameters range of the test simulation, and provide a guarantee for the heat transfer and ablation test research of thermal insulation materials in the high temperature aerothermal environment.
机译:在超音速飞行时,飞机将面临严重的空气动力学加热。它的表面材料必须经过近距离实际战斗的空气热量消融测试。测试的关键是在地面上创建等效的空气环境。目前,用于模拟空气环境的主要方法是石英灯加热,氧乙烯预混燃烧,发动机排气和高焓风隧道。高焓风隧道可以建立最接近实际状态的空气热环境,但实验成本太高,一些参数不能满足条件。本文总结了空气环境的试验模拟方法,通过分析实验参数,提出了一种更准确的试验参数的相似性标准。在标准中,当难以同时保证相同的恢复焓和冷壁热流时,必须将平等的热壁热通量作为基本原理,然后是试验气体的恢复温度应根据地面测试条件下的对流传热系数调整,以满足测试要求。本文还设计了一种新型的空气环境仿真装置,具有更简单的操作,更低的成本和更简单的参数调整。使用本文提出的方法和设备进行了超声波抗击环境中的材料消融实验。实验结果与弧风隧道试验的实验结果接近。这表明所提出的测试装置和参数相似性方法不仅可以模拟高温的空气环境,还可以拓宽测试模拟的参数范围,并为热绝缘材料的传热和消融测试研究提供了保证高温空气温度环境。

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