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目的为了更好地解决高超声速飞行器舵、翼前缘及头锥等气动热环境恶劣区域的热防护问题。方法采用主动式热疏导技术,以高温液态合金为工质,设计并制作具有主动式热疏导功能的尖化前缘金属试验模型(R=5 mm)。根据模型外尺寸设计加工一套石英灯仿形加热器和热流测试模型,开展地面热环境模拟试验。结果试件在前缘中心温度530℃左右时具有瞬态启动特性。前缘中心和大面积中心最大辐射热流密度分别为1000 kw/m~2和580 kw/m~2,试件在该环境中长时间受热状态下仍具有较好的热疏导能力。试验后试件无工质泄漏和结构破坏,具有一定的可重复使用性。结论可以此热疏导方式结合现有成熟热防护技术进一步开展工程设计与应用。
Aim In order to solve the problem of thermal protection in harsh aerodynamic environments such as hypersonic rudder, wing leading edge and nose cone, Methods An active leading thermal conductivity technique was used to design and fabricate a sharp leading edge metal test model (R = 5 mm) with high temperature liquid alloy as working fluid. According to the size of the model design and processing of a quartz lamp profiling heater and heat flow test model to carry out ground thermal environment simulation test. Results The specimen has a transient start-up behavior at a temperature of about 530 ° C at the leading edge. The maximum radiative heat flux density of the front center and the large center are 1000 kw / m ~ 2 and 580 kw / m ~ 2, respectively. The specimens still have good thermal conductivity in long time heating in this environment. After the test specimen no leakage and structural damage, with some reusability. Conclusions The design and application of this project can be further carried out with this thermal grooming method combined with the existing mature thermal protection technology.