摘要
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 )
In this paper,response analysis and experimental verification is accomplished for reentry vehicle shell subjected to aerodynamic noise using experimental results and MSC/NASTRAN software.The satisfactory result is obtained.Within the range of 0-1000Hz,the relative error of computational result is less than 30% in comparison with experimental results of RMS of acceleration response.From the proceeding response analysis and experimental verification,it is shown that two steps must be followed to acquire satisfactory computational results.Firstly,according to the experimental results of modes,dynamic computational model is modified to ensure the accuracy of the lower order modal parameters.Secondly,FEM meshing must satisfy some fine standard to ensure modal number including the higher order modes (avoiding the omission of the higher order modes)
出处
《强度与环境》
2002年第2期5-9,共5页
Structure & Environment Engineering
