中文摘要：

研究了战斗机垂尾在跨声速范围的非线性气动弹性行为和弹性载荷特性。针对飞机垂尾，计算了飞机垂尾的颤振边界，通过CFD/CSD耦合时域内推进结构运动方程，得到弹性结构的响应历程，并记录每一时刻的气动载荷和结构惯性载荷，将气动载荷信息转换到 CSD的结点上，加载到结构模型上进行瞬态响应分析，得到结构的动应力响应，计算给出了0°侧滑角时不同马赫数下的颤振边界和Ma=0.9、侧滑角2°和10°时的非定常气动载荷与非定常惯性载荷和弹性载荷的时域响应，分析了惯性载荷、气动载荷和弹性载荷对颤振的影响以及方向舵对垂尾颤振的影响。

英文摘要：

This study focuses on nonlinear behavior of aeroelasticity and dynamic elastic load of vertical tail on fighter aircraft in a state of transonic speed.A time domain coupled CFD/CSD strategy is introduced and a method of calculating elastic load is presented by using this strategy.The analysis is based on numer-ical results of flutter boundary of 0°sideslip angle under different mach numbers and unsteady aeroelastic load at 0.9 Mach、sideslip angle of 2°and 10°,and the effect of rudder on flutter is detected.Dynamic re-sponses of inertial load and elastic load are also available.