飞翼布局飞行器由于短周期模态频率较高，容易与结构的低阶弹性模态耦合从而引发体自由度颤振问题。针对当前体自由度颤振试验手段存在的不足，提出飞翼构型地面颤振试验方法，通过多激振器协同激励模拟结构刚体与弹性模态非定常气动力，实现体自由度颤振地面测试，建立基于计算流体力学（CFD）与面元法混合建模的刚弹耦合非定常气动力影响系数矩阵重构方法，可考虑机体厚度等效应影响，同时模型计算效率与常规面元法相当，满足体自由度颤振仿真分析及地面试验的要求，搭建了试验系统并针对飞行试验模型开展了地面试验，地面试验结果与飞行试验结果对比，颤振边界及颤振形态均吻合良好，证明了该技术在刚弹耦合气动弹性领域应用的可行性。

The flying-wing aircraft has a high short-period modal frequency， which is prone to coupling with the low-order elastic modes of the structure， thereby causing the body freedom flutter. In response to the shortcomings of the current body freedom flutter test methods， a ground flutter test method for the flying-wing aircraft is proposed. Through the coordinated excitation of multiple vibration exciter to simulate the unsteady aerodynamic forces of the rigid body and elastic modes of the structure， the ground test for the body freedom flutter is realized. A reconstruction method for the unsteady aerodynamic influence coefficient matrix of the rigid-elastic coupling based on the hybrid modeling of Computational Fluid Dynamics （CFD） and panel method is established， which can consider the effects of the aircraft thickness and other factors. In addition， this method’s calculation efficiency is comparable to that of the panel method， meeting the requirements of body freedom flutter analysis and ground tests. The ground test system was built and tests were carried out for the airplane model. The comparison of the ground test results with the flight test results shows that the flutter boundary and flutter modality are in good agreement， proving the feasibility of this technology in the field of rigid-elastic coupled aeroelasticity.