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超声速飞行器油箱受气动加热影响,其外表面不断与来流进行热交换,油箱内部的燃油也会受到气动加热影响而使燃油温度及供油温度不断升高,应用全方程控制加热试验技术,在地面进行超声速气动加热模拟条件下飞行器油箱传热试验,在试验中经参数测量获得了油箱供油特性,结果表明全方程控制加热试验技术准确模拟真实油箱气动加热状态,为油箱供油系统设计及性能分析提供试验验证方法,测量得到的油箱内燃油温度为277℃,供油温度为126℃,满足冲压发动机不能高于150°C的要求。
Supersonic aircraft fuel tank by the impact of aerodynamic heating, the outer surface of the constant heat exchange with the incoming flow, the fuel tank inside will be affected by the aerodynamic heating of the fuel temperature and fuel supply temperature continues to rise, the application of full range of controlled heating test technology, The heat transfer test of the tank under the ultrasonic aerodynamic heating simulation was carried out on the ground. The fuel supply characteristics of the tank were obtained through the parameter measurement in the experiment. The results show that the full-scale controlled heating test technology accurately simulates the actual heating state of the fuel tank. Performance analysis to provide experimental verification methods, the measured fuel tank fuel temperature is 277 ℃, the supply temperature is 126 ℃, to meet the stamping engine can not be higher than 150 ° C requirements.