Aero-thermo-elastic Numerical Calculation and Analysis of Spinning Rocket

作     者：陈东阳 Laith K.Abbas 芮筱亭 Marzocca Piergiovanni 王国平 

作者机构：Institute of Launch DynamicsNanjing University of Science and Technology Department of Mechanical and Aerospace EngineeringThe Wallace H.Coulter School of EngineeringClarkson University 

出 版 物：《Transactions of Nanjing University of Aeronautics and Astronautics》 (南京航空航天大学学报（英文版）)

年 卷 期：2014年第31卷第6期

页      面：681-687页

核心收录：

学科分类：08[工学] 082504[工学-人机与环境工程] 0825[工学-航空宇航科学与技术] 

基　　金：Supported by the National Natural Science Foundation of China(11102089) 

主　　题：ANSYS Workbench numerical calculation thermal stress spinning 

摘      要：The application of computational fluid dynamics/computational solid method(CFD/CSM)on solving the aero-thermo-elastic problem of spinning rocket is ***,the aerodynamic coefficients of a rocket are calculated,and the results are compared with the available experimental data,which verified the accuracy of the CFD ***,analysis is carried using ANSYS Workbench multi-physics coupling platform,which includes fluid,thermal,and structural *** results show that spinning causes a significant effect on the deformations and ***,thermal stresses due to high temperature at the rocket warhead and tail edges have a dominated effect,even more than those produced by aerodynamic ***,this important outcome should be taken into consideration during the rocket design stages.