作者以一个小展弦比的三角机翼模型为对象,完成了颤振主动抑制系统的试验研究。风洞试验结果说明,采用颤振主动抑制控制系统后,机翼的颤振临界速度可提高37％。文中还提出了气动弹性系统特性,包括(开环)超临界频响函数的测试方法,试验结果和理论分析结果较为一致。 With a small aspect ratio triangular wing model as an object, the author completed the experimental research on the active suppression system of flutter. Wind tunnel test results show that the flutter active suppression control system, the wing flutter critical speed can be increased by 37%. The paper also presents the characteristics of aeroelastic system, including (open-loop) supercritical frequency response function test method, the experimental results and theoretical analysis results are more consistent.