开裂角对阻力方向舵颤振特性的影响

摘要

The drag rudder is a kind of very effective yaw control devices for tailless aircrafts. When yaw control is pro-cessing, the control surfaces have large delfection, which produce very complex lfuid motion, such as separation lfow, vortex phenomena etc. The unsteady aerodynamic becomes too dififcult to use classical methods to analyze aeroelas-tic problems. Fluid-Structure Interaction method was used to solve the aeroelastic problems of two-dimension drag rudder. The results show that lfutter velocities extend with increasing split angles. Because large split angles produce separation lfow in the windward zone and dead lfow in the leeward, which decreases the unsteady aerodynamic inlfu-encing coefifcient of drag rudder, a larger velocity is needed that can stimulate the drag rudder to occur lfutter.%对于无垂尾飞翼式布局飞机，阻力方向舵是一种十分有效的偏航控制装置。偏航控制时，舵面大角度偏转，引起气流分离、涡等复杂流场运动，非定常气动力复杂。计算气动弹性学科提出流固耦合求解方法，以期用于阻力方向舵气动弹性问题的求解。本文采用基于CFD技术的流固耦合方法求解阻力方向舵二维气动弹性问题，计算结果表明，随着开裂角的增大，阻力方向舵的颤振速度增加。对阻力方向舵气动特性进行了计算分析，结果表明阻力方向舵开裂，舵面背风区形成死水区，舵面非定常气动力影响系数减小，阻力方向舵开裂角越大，其颤振速度越大。