中南大学学报（自然科学版）2012，Vol.43Issue(9)：3450-3454,5.
高超声速二元机翼迟滞非线性热颤振
Hypersonic airfoil aerothermoelastic analysis with hysteretic nonlinearities
摘要
Abstract
The aerothermoelastic of hypersonic airfoil with hysteretic nonlinearities was analyzed, and the third-order piston theory aerodynamic was employed to evaluate the unsteady aerodynamic loads. Also the loss of torsional stiffness induced by aerodynamic heating was considered. The heat-flutter velocity with various thickness ratios was studied. The research results show that the linear flutter velocity increases with the increase of thickness ratios. The airfoil dynamic responses involving limit cycle oscillation, bifurcation behavior are observed over parameters of aerothermoelastic system by time history curve and poincare map. It is found that the bifurcation velocity is less than linear flutter velocity, and the limit cycle oscillation amplitude increases as flight velocity increases.关键词
气动弹性/气动热弹性/迟滞非线性/高超声速/气动加热Key words
aeroelastic/aerothermoelastic/hysteretic nonlinear/hypersonic/aerodynamic heating分类
航空航天引用本文复制引用
钮耀斌,王中伟..高超声速二元机翼迟滞非线性热颤振[J].中南大学学报（自然科学版）,2012,43(9):3450-3454,5.基金项目
国家高技术研究发展计划("863"计划)项目(2011AAXXXX108) （"863"计划）
国防科技大学优秀研究生创新资助项目(B120107) （B120107）
