本文利用再入飞行器壳体气动噪声试验结果和MSC/NASTRAN软件完成了再入飞行器壳体复杂结构气动噪声的响应分析与试验验证 ,取得了令人满意的结果 :0 - 10 0 0Hz范围的振动加速度响应均方根值的计算值相对试验测量值的相对误差低于 30 %。响应分析和试验验证的研究表明 :利用模态试验结果修正动力学计算模型保证其低阶模态参数准确 ,同时有限元网格必须满足一定的细化标准 ,保证包括高阶模态在内的模态数 (避免高阶模态的遗漏 )才能得到符合实际的计算结果 In this paper, the aerodynamic noise of the reentry vehicle shell and the MSC / NASTRAN software are used to analyze and test the aerodynamic noise of the reentry vehicle shell. The satisfactory results are obtained: the vibration in the range of 0-1000Hz The rms value of the acceleration response is less than 30% relative to the experimental measurement. Response analysis and experimental verification show that modal test results can be used to correct dynamic model to ensure low-order modal parameters are accurate. At the same time, the finite element mesh must meet certain refinement criteria to ensure modalities including high-order modal The number (to avoid the omission of high-order mode) in order to get the actual calculation results