Influence of rudder shaft location on the aeroelastic characteristics of an all-moving rudder is investigated. The modals of the rudder are analyzed by means of finite element method. unsteady aerodynamic force is calculated using local piston theory. The dynamic equations are established based on Lagrange’s equation. Results show that the destabilizing form changes from flutter to divergence with the rudder shaft location moving along the root chord from the leading edge to the trailing edge. The location of the destabilizing form changing moves backward with the increasing of the attack angle. The flutter critical dynamic pressure decreases initially and then increases slightly with the rudder shaft moving backward in front of the changing location. While the divergence critical dynamic pressure decreases monotonously with the rudder shaft moving backward behind the changing location.%研究舵轴位置对全动舵面气动弹性特性的影响，用有限元方法分析舵面模态，当地流活塞理论计算非定常气动力，应用Lagrange方程，建立基于模态坐标运动方程。结果表明：当舵轴在根弦相对位置从前向后移动过程中，失稳形态由颤振转变为发散，并引起临界动压突变现象。失稳形态转变位置会随着攻角增大而逐渐后移。在转变位置之前，颤振临界动压随着舵轴后移，呈现先减小后小幅度增大趋势；在转变位置之后，发散临界动压随着舵轴后移单调减小。
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