摘要
针对现代民用飞机翼吊发动机机翼跨声速颤振问题,建立了带超临界翼型、大展弦比后掠和翼吊一个发动机构型的机翼模型,通过偶极子格网(DLM)气动力修正方法、升力线斜率系数修正方法、ZTAIC方法和高速颤振模型风洞试验方法研究了飞机翼吊发动机跨声速颤振特性。分析了马赫数和阻尼对跨声速颤振特性的影响。结果表明:翼吊发动机机翼具有三种典型颤振,即机翼弯曲扭转耦合模态颤振、机翼面内振动模态颤振和发动机与机翼耦合模态颤振;马赫数对翼吊发动机机翼跨声速颤振会产生不利影响,主要表现在跨声速区域显著降低机翼跨声速临界颤振动压;结构阻尼对机翼-发动机耦合小阻尼颤振模态的影响显著,增大阻尼可以显著提高其颤振动压。
Transonic flutter characteristics of wing with engine mounted were investigated for civil aircrafts. A cantilevered high aspect ratio supercritical wing with engine mounted was modeled by finite element method. A method for computing the transonic unsteady aerodynamics was using a transonic equivalent strip（ ZTAIC）,the weighted method by correcting the aerodynamic influence coefficients（ AIC） using doublet lattice method（ DLM）,lift curve slope compressibility correct method and high-speed flutter model transonic wind tunnel test method were used to conduct transonic flutter research. The Mach number and structure damping effect on wing transonic flutter dynamic characteristics were evaluated. The results show that there are three classic flutter modes which are the coupling between wing vertical bending and wing torsion,wing chordwise bending,and the coupling between wing bending and engine nacelle.In transonic region,increasing Mach number significantly reduces the transonic flutter dynamic pressure.Increasing structure damping can significantly increase flutter dynamic pressure for wing/nacelle flutter mode.
出处
《飞行力学》
CSCD
北大核心
2018年第1期79-83,共5页
Flight Dynamics
关键词
跨声速
颤振
机翼
马赫数
transonic
flutter
wing
Mach number
