TY - GEN
T1 - Study on areothermoelastic for hypersonic all moving control surface
AU - Ye, Kun
AU - Ye, Zhengyin
AU - Zhang, Qing
AU - Main, Haris Hameed
AU - Wang, Gang
AU - Qu, Zhan
N1 - Publisher Copyright:
© 2016 IEEE.
PY - 2016/3/9
Y1 - 2016/3/9
N2 - In this paper, the effect of the aerodynamic heating on shaft and the connection between the shaft and the body on areothermoelasticity for hypersonic all moving control surface is studied. A loosely coupled framework on aerothermoelastic stability boundary calculation for hypersonic vehicles is developed. Firstly, based on the computational fluid dynamics (CFD) technology, Navier-Stokes equation is solved to get the thermal environment. Then transient heat transfer of structure is analyzed. After that structural mode is analyzed under the effect of structure's thermal stress caused by temperature gradient and material property decrease caused by high temperature. Then structural mode is interpolated to the aerodynamic grids. Finally, Euler equation is solved to get flow parameters, and based on CFD local piston theory, aerothermoelasticity is analyzed in state space. The results show that: the heat transfer process and temperature distribution of the shaft structure are influenced obviously by the effect of the aerodynamic heating on shaft and the connection between the shaft and the body, and natural frequency and flutter characteristics are affected significantly, too. For the model in this paper, the effect of the aerodynamic heating on shaft and the connection between the shaft and the body on aeroelastic stability boundary is 8.31% and 6.87%, respectively.
AB - In this paper, the effect of the aerodynamic heating on shaft and the connection between the shaft and the body on areothermoelasticity for hypersonic all moving control surface is studied. A loosely coupled framework on aerothermoelastic stability boundary calculation for hypersonic vehicles is developed. Firstly, based on the computational fluid dynamics (CFD) technology, Navier-Stokes equation is solved to get the thermal environment. Then transient heat transfer of structure is analyzed. After that structural mode is analyzed under the effect of structure's thermal stress caused by temperature gradient and material property decrease caused by high temperature. Then structural mode is interpolated to the aerodynamic grids. Finally, Euler equation is solved to get flow parameters, and based on CFD local piston theory, aerothermoelasticity is analyzed in state space. The results show that: the heat transfer process and temperature distribution of the shaft structure are influenced obviously by the effect of the aerodynamic heating on shaft and the connection between the shaft and the body, and natural frequency and flutter characteristics are affected significantly, too. For the model in this paper, the effect of the aerodynamic heating on shaft and the connection between the shaft and the body on aeroelastic stability boundary is 8.31% and 6.87%, respectively.
KW - aerodynamic heating
KW - areothermoelasticity
KW - control surface
KW - Hypersonic
KW - local flow piston theory
UR - https://www.scopus.com/pages/publications/84978110523
U2 - 10.1109/IBCAST.2016.7429920
DO - 10.1109/IBCAST.2016.7429920
M3 - 会议稿件
AN - SCOPUS:84978110523
T3 - Proceedings of 2016 13th International Bhurban Conference on Applied Sciences and Technology, IBCAST 2016
SP - 467
EP - 475
BT - Proceedings of 2016 13th International Bhurban Conference on Applied Sciences and Technology, IBCAST 2016
A2 - Zafar-uz-Zaman, Muhammad
PB - Institute of Electrical and Electronics Engineers Inc.
T2 - 13th International Bhurban Conference on Applied Sciences and Technology, IBCAST 2016
Y2 - 12 January 2016 through 16 January 2016
ER -