热环境下某飞行器振动特性分析与模型修正

Vibration Characteristics Analysis and Model Modification of an Aircraft in Thermal Environment

基于结构热振动理论,针对某型复合材料结构飞行器建立其热环境下结构动力学计算的有限元模型。对该结构进行结构动态特性分析,并结合地面常温的模态实验数据对该有限元模型进行优化。得到该结构常温下的振动特性及其受给定温度场影响的变化情况。针对该类复合材料结构建模及模型修正的方法,给出较为合理的优化方法及优化结果,对工程实际有一定的指导意义。

The finite element model of an aircraft with complex composite structures was constructed for dynamic simulation in thermal environment. Based on the analysis of its dynamic characteristics, the FEM model was optimized according to the mode-test data in the natural temperature environment on the earth. The vibration characteristics of the aircraft were obtained. Change of the characteristics due to the affect of the temperature field was also obtained. The methods of the FEM model construction and optimization of the composite structures of the aircraft were presented using MSC. Nastran SOL 200, which may be useful for practical engineering projects.