类F-16飞行器风洞虚拟飞行试验研究

为研究高性能战斗机在大迎角机动飞行时复杂的非定常流动现象和运动-控制耦合现象，研制了三自由度风洞虚拟飞行试验系统，开展了类F-16飞行器模型风洞虚拟飞行试验。在小迎角试验中完成模型短周期运动模态模拟和控制律验证，在大迎角试验中测量到俯仰运动失稳现象，在负迎角试验中测量到横航向耦合失稳现象。研究表明:在横航向耦合失稳时，采用副翼增稳滚转通道难以恢复横航向稳定性，且可能发生运动-控制耦合振荡，而通过升降舵机动改变迎角可有效恢复横航向稳定性。

Wind tunnel based virtual flight testing research of F-16 fighter

A three degree-of-freedom (3-DOF) Wind Tunnel Based Virtual Flight Test (WTBVFT) system is developed to study unstable aerodynamic phenomena and maneuver characteristics coupling with motion of high-performance fighters maneuvering at high angle of attack. Based on this system, a series of 3-DOF virtual flight tests of F-16 fighter are performed. As the results, the short-time modes of flight dynamics are simulated from wind tunnel tests with small angle of attack, and control law are validated in those tests. Then an instability phenomenon in pitch is detected from tests with high angle of attack. A group of lateral-directional unstable aerodynamic-coupling motions are detected from tests when angle of attack is less than zero. In these tests, augmentation control of aileron cannot recover lateral-directional stability of flight, but always leading to control coupling motion. It is more effective to adopt elevator control to change angle of attack to recover the lateral-directional stability.