摘要
针对折叠舵的气动弹性问题,考虑三维翼型的非定常气动力,研究了弯曲和扭转两维间隙非线性颤振分析方法。时域仿真结果表明:间隙非线性环节将导致系统出现极限环振荡;频率散布的下限值决定亚临界颤振速度,频率散布的上限值决定发散速度;模态振型节线的方向同样影响亚临界颤振速度和发散速度。
According to the aeroelasticity of folding rudder, by considering the unsteady aerodynamic of three dimensional wing, nonlinear flutter analysis method with two dimensional freeplay of bend and torsion is studied. The time domain simulation results show that the freeplay nonlinearity will result in limit cycle oscillations of the system. The lower frequency of dispersed frequencies determines the subcritical flutter speed. The upper frequency of dispersed frequencies decides the divergent velocity. The di- rection of the vibration mode nodal line also affects the subcritical flutter speed and divergent velocity.
出处
《现代防御技术》
北大核心
2013年第1期15-19,30,共6页
Modern Defence Technology
关键词
折叠舵
二维间隙非线性
非定常气动力
颤振
folding rudder
two-dimensional freeplay nonlinearity
unsteady aerodynamic
flutter
