某战斗机高速全模颤振风洞试验研究  

Investigation on Full-model Flutter of a Certain Fighter Plane in High-speed Wind Tunnel Test

作　　者：郭洪涛[1] 路波[1] 余立[1] 杨兴华[1] 罗建国[1] 吕彬彬[1] 

机构地区：[1]中国空气动力研究与发展中心高速空气动力研究所,四川绵阳621000

出　　处：《航空学报》2012年第10期1765-1771,共7页Acta Aeronautica et Astronautica Sinica

摘　　要：为了验证高速风洞全模颤振试验技术以及获取某战斗机颤振安全边界,运用风洞试验的方法研究了某战斗机全模颤振特性,重点考察了模型在支撑系统上的稳定性、安全性以及典型颤振特性。结果表明:采用悬浮支撑系统可以使颤振模型具有除轴向以外的5个方向的运动自由度以及较好的稳定性和安全性;跨声速时的非线性气动力与速压较高时的结构非线性对全机颤振特性有较大影响,导致模态参数与颤振稳定性参数随速压呈非线性变化;振动波形图显示了该模型颤振形式为缓和型颤振,验证了模型设计时的计算结果。In order to validate the flutter testing technology for high-speed wind tunnel and obtain the flutter safety limit of a fighter plane, the full-model flutter characteristics of the fighter plane are investigated based on wind tunnel test. The key points of investigation focus on the stability and safety of the model and support system, and the typical flutter characteristics of the full-model. The results reveal that the freedom degrees of the model motion are not restricted by the support system except for axis direction and the system is stable and safe during testing. The flutter characteristics are influenced to a great extent by the non-linear aerodynamic forces at the transonic regime and the non-linear elastic forces at higher dynamic pres- sures, and the non-linear relationship between stability parameters and dynamic pressure also resulted from them. The plot of vibration time history show that the flutter type of the full-model is a tempered flutter and validated the calculation results when the model is designed.

关 键 词：全模颤振 气动弹性 悬浮支撑系统 风洞试验 战斗机 

分 类 号：V215.34[航空宇航科学与技术—航空宇航推进理论与工程]