摘要
针对翼．身组合体飞行器面对称布局的特点，利用模态振型的对称和反对称性，以分枝模态法建立结构的运动微分方程，结合CFD的当地流活塞理论计算飞行器的非定常气动力，建立飞行器全机组合体的气动弹性数学模型。对飞行器进行了来流为1．5～7马赫数下的颤振分析，结果与全CFD／CSD耦合时域仿真结果较好吻合，验证了本文方法在工程设计中的有效性和可行性。本文方法的效率在相同精度下比CFD／CSD耦合的时域方法高100倍。
To establish the aero-elastic model of wing-fuselage vehicle,the structural dynamic model is founded by branch mode method,which depends on the symmetrical and antisymmetrical mode shape.Unsteady aerodynamic force of vehicle is calculated by the local piston theory based on CFD.The flutter boundary of Ma equals to 1.5~7 results by CFD-based local piston theory agree well with those by the CFD/CSD direct coupling method.The results obtained demonstrate that the approach developed is suitable for the flutter analysis of a wing-fuselage complete vehicle.
出处
《应用力学学报》
CAS
CSCD
北大核心
2011年第6期613-617,674,共5页
Chinese Journal of Applied Mechanics
基金
国家自然科学基金(90716001)
总装"十一五"航天支撑技术项目基金(617010602)
关键词
气动弹性
颤振
翼-身组合体
全机
当地流活塞理论
aero-elasticity,flutter,wing-fuselage,complete vehicle,local piston theory.
