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 

机构地区：[1]Institute of Launch Dynamics,Nanjing University of Science and Technology [2]Department of Mechanical and Aerospace Engineering,The Wallace H.Coulter School of Engineering,Clarkson University

出　　处：《Transactions of Nanjing University of Aeronautics and Astronautics》2014年第6期681-687,共7页南京航空航天大学学报（英文版）

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

摘　　要：The application of computational fluid dynamics/computational solid method(CFD/CSM)on solving the aero-thermo-elastic problem of spinning rocket is introduced.Firstly,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 output.Then,analysis is carried using ANSYS Workbench multi-physics coupling platform,which includes fluid,thermal,and structural solvers.The results show that spinning causes a significant effect on the deformations and stresses.Furthermore,thermal stresses due to high temperature at the rocket warhead and tail edges have a dominated effect,even more than those produced by aerodynamic forces.Consequently,this important outcome should be taken into consideration during the rocket design stages.The application of computational fluid dynamics/computational solid method （CFD/CSM） on solving the aero-thermo-elastic problem of spinning rocket is introduced. Firstly, 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 output. Then, analysis is carried using ANSYS Workbench multi-physics coupling platform, which includes fluid, thermal, and structural solvers. The results show that spinning causes a significant effect on the de formations and stresses. Furthermore, thermal stresses due to high temperature at the rocket warhead and tail edges have a dominated effect, even more than those produced by aerodynamic forces. Consequently, this important outcome should be taken into consideration during the rocket design stages.

关 键 词：ANSYS Workbench numerical calculation thermal stress SPINNING 

分 类 号：V448.15[航空宇航科学与技术—飞行器设计]