中文摘要：

为了满足飞行的确认要求，为先进飞机控制法律，一条风隧道基于测试的虚拟飞行在一条低速度风隧道被实现了。A 3-degree-of-freedom 万向节，腹地在模型安装了，与飞机的一个活跃地控制的动态地类似的模型一起被使用，它与惯性的测量单位，态度和标题引用系统，嵌入的计算机和伺服致动器被装备。和流动域，操作符和在靠近环的测试电路上面做的实时控制系统的模型，能到空气动力学的时刻自由地在它的重心附近被旋转，。模型在纵的方向是静态地不稳定的，并且它能与飞行控制法律的控制扩大的功能在风隧道稳定地飞。试验性的结果显示模型对操作员指令作出回应很好。在测试的模型的反应与模拟结果显示出合理同意。攻击的角度的反应的差别是不到 0.5

英文摘要：

To satisfy the validation requirements of flight control law for advanced aircraft,a wind tunnel based virtual flight testing has been implemented in a low speed wind tunnel.A 3-degree-offreedom gimbal,ventrally installed in the model,was used in conjunction with an actively controlled dynamically similar model of aircraft,which was equipped with the inertial measurement unit,attitude and heading reference system,embedded computer and servo-actuators.The model,which could be rotated around its center of gravity freely by the aerodynamic moments,together with the flow field,operator and real time control system made up the closed-loop testing circuit.The model is statically unstable in longitudinal direction,and it can fly stably in wind tunnel with the function of control augmentation of the flight control laws.The experimental results indicate that the model responds well to the operator＇s instructions.The response of the model in the tests shows reasonable agreement with the simulation results.The difference of response of angle of attack is less than 0.5°.The effect of stability augmentation and attitude control law was validated in the test,meanwhile the feasibility of virtual flight test technique treated as preliminary evaluation tool for advanced flight vehicle configuration research was also verified.