高速巡航导弹翼面结构热-振联合试验研究

 由于高速巡航导弹飞行速度快、滞空时间长,在气动加热引起弹翼、整流罩和弹体等部件外表面温度升高的同时,还会伴随长时间的剧烈振动。气动加热产生的热环境会使材料和结构的弹性模量、刚度等力学性能发生明显变化,复杂的机动飞行过程又会使结构中出现较大的温度梯度,引起热应力场的改变,进而对导弹结构的固有振动特性带来严重的影响。以高速巡航导弹翼面结构为研究对象,进行了热环境下的翼面结构热-振联合试验,获得了不同温度条件下翼面结构固有频率等振动特性的变化规律,为巡航导弹弹翼结构在高速、热振动环境下的安全设计提供了可靠依据。

Research on Thermal-vibration Joint Test for Wing Structure of High-speed Cruise Missile

High-speed cruise missiles fly at high speeds for a long time.During a high-speed flight,the surface temperatures of the wing,fairing and projectile rise rapidly because of aerodynamic heating,which is accompanied by serious structural vibration.The aerodynamic heating causes significant changes in the mechanical properties of the structure,and the high temperature gradients produced by the complex maneuver-flight generate thermal stress.They both affect seriously the characteristics of the structure’s natural vibration.In this paper,a joint thermal-vibration testing is performed on the wing structure of a cruise missile,and the vibration characteristics of the wing structure(e.g.,the natural frequency) at various temperatures are obtained.The experimental results can provide a reliable basis for the safety design of cruise missiles under high-speed,high-temperature and vibration conditions.