考虑气动加热的翼面结构热模态试验方法研究  

Thermal modal test method for a wing structure considering aerodynamic heating

作　　者：刘浩[1] 李晓东[1] 杨文岐[1] 孙侠生[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《振动与冲击》2015年第13期101-108,共8页Journal of Vibration and Shock

基　　金："十二五"航空支撑技术基金项目(61901030203)

摘　　要：受热结构的热模态特性试验研究对高超声速飞行器设计校核和飞行安全具有重要的意义。建立了一套考虑气动加热影响的结构热模态试验系统,依据气动加热数值计算得到的结构温度场计算加热温度跟踪控制系统参数,对飞行过程中的瞬态热环境进行模拟,测量各个加热温区的温度随加热时间的变化,验证了加热温度控制的精确性。将智能PID控制技术与传统相位共振方法相结合,提出了模态频率自动跟踪方法,使传统相位共振方法的应用范围扩展至瞬态热环境下时变结构系统的模态试验领域。设计了一个切尖三角形薄板翼面结构试验件,并采用模态频率自动跟踪方法对该结构进行热模态试验,获得了结构的前四阶模态频率随加热时间的变化,并与结构有限元数值计算结果进行比较,试验与计算结果吻合得很好,验证了模态频率自动跟踪方法对热模态测试问题的有效性和准确性。分别通过对瞬态和稳态热环境下结构模态频率试验和计算结果的分析,探讨气动加热产生的结构瞬态温度场对模态频率影响的机理,解释了模态频率随加热时间变化趋势的内在原因。It is important to investigate the thermal modal test of a wing structure in design and flight of modern hypersonic flight vehicles.Here,a strucutre’s thermal modal test system considering aerodynamic heating was established. The temperature control parameters depending on the structure’s transient temperature field calculated with numerical analysis were used to simulate the transient thermal environment.The temperature changings with heating time were measured,the accuracy of temperature control was validated.The modal frequency auto-tracing method was proposed by combining the intelligent PID （proportion integration differentiation ） control technology with the traditional phase resonance method,the application range of the traditional phase resonance method was expanded into the modal parameter identification of time-dependent structural dynamic systems under the transient thermal environment.The modal frequency auto-tracing method was used to measure the first four thermal modal frequencies of a triangular wing structure in a thermal modal test.The test results agreed well with those using FEM （finite element method）.The results indicated that the modal frequency auto-tracing method for time-dependent structures’modal parameter identification is effective and correct. In addition,the modal frequencies of thermal structures under steady temperature field were measured in a thermal modal test,the results also agreed well with those of the numerical computation.The reason of modal frequencies of time-dependent thermal structures changing with heating time was explained by comparing the identification results under transient temperature field with those under steady temperature field.

关 键 词：高超声速飞行器 气动加热 翼面结构 热模态试验 模态频率自动跟踪 相位共振法 

分 类 号：V416.5[航空宇航科学与技术—航空宇航推进理论与工程]