疏导式热防护在翼前缘中的应用探索

针对高超声速飞行器飞行时翼前缘存在着严重的气动加热问题，为了保证翼前缘的尖锐外形，提出疏导式热防护结构，利用内置高温热管结构为翼前缘提供热防护。采用数值模拟和电弧风洞试验的方法对翼前缘疏导式结构进行了分析，得到翼前缘内置高温热管具有的防热效果。数值模拟结果表明在一定热环境条件下，翼前缘驻点温度下降了304K，尾部最低温度升高了130K，实现了热流从高温区到低温区的疏导，减弱了翼前缘的热载荷，强化了翼前缘的热防护能力。通过电弧风洞试验可以获得相同的热防护结果，并且在一定飞行条件下高温热管可以自适应启动，验证了数值模拟方法的准确性以及翼前缘内置高温热管疏导式热防护结构的可行性。

HEAT-PIPE-COOLED THERMAL PROTECTION FOR THE LEADING EDGE OF THE WING

In view of the severe aerodynamic heating on the wing leading edge of the hypersonic vehicle, in order to ensure the sharp shape of the leading edge of the wing, a dredged thermal protection structure is proposed, and the built-in high-temperature heat pipe structure is used to provide the thermal protection for the leading edge of the wing. The numerical simulation and the arc wind tunnel test method are used to analyze the wing leading edge dredging structure, and to reveal the heat protection effect of the built-in high-temperature heat pipe at the leading edge of the wing. The numerical results show that under certain thermal conditions, the temperature on the leading edge of the wing decreases by 304K, and the minimum temperature on the tail increases by 130K. The heat flow from the high temperature zone to the low temperature zone is dredged, and the thermal load on the leading edge of the wing is weakened. The thermal protection for the leading edge of the wing is enhanced. The same result is obtained by the arc wind tunnel test. And the high temperature heat pipe can be adaptively started under certain flight conditions, which verifies the accuracy of the numerical simulation method and the feasibility of the built-in high temperature heat pipe dredging thermal protection structure at the leading edge of the wing.