高超声速飞行器结构热模态试验国外进展

The review of the high temperature modal test for the hypersonic vehicle

高超声速飞行器在巡航/再入阶段受到严酷的气动加热效应,极高的温度及温度梯度,改变飞行器结构热物理参数和力学性能,导致结构弯曲、扭转刚度下降,颤振安全边界降低,影响飞行器结构的可靠性。热环境下的结构模态特性,作为反映气动加热对结构影响的重要参数,在指导、验证此类飞行器的设计中具有重要意义。20世纪中期以来,NASA Langley、Dryden等研究中心分别针对金属和复合材料壁板、X-15翼舵、X-34发动机喷管等结构开展热模态试验方法研究与试验验证,近期Dryden研究中心针对X-37方向舵开展热模态试验的探索研究。系统综述了国外开展的热模态试验方法、试验设施和试验结果,总结热模态试验中的工程问题和研究方向,对于国内热模态试验技术的发展、飞行器结构高温性能评估等均具有重要的指导意义。

Future hypersonic aircraft will be, exposed to increasmg aerothermal load dunng cruise anti reentry phases. High surface temperatures and temperature gradients can affect the vibratory characteristics and stability of aircraft. Thermal modal testing techniques can give quantitative analysis for the effect of the thermal load. Since 1950s, NASA Langley and Dryden have carried out a lot of related research. Many experiments have done for the metal and the compound panels, the X-15 wing, the X-34 Fastrac Composite Rocket Nozzle. Recently, NASA Dryden Flight Research Center performed the high-temperature modal survey of the carbon-silicon carbide ruddervator subcomponent test article, which is a truncated version of the X-37 full scale hot structure control surface. This paper discusses the high temperature modal survey conducted during the last 60 years. It can support the development of thermal vibration test in China.