机翼双梁模型的动力学修正及应用  

Dynamic modification and application of wing double-beam model

作　　者：贺尔铭[1] 陈熠[1] 李玉龙[1] 扈西枝[2] 韩峰[2] 

机构地区：[1]西北工业大学,西安710072 [2]上海飞机设计研究院,上海200232

出　　处：《应用力学学报》2013年第3期367-372,475,共6页Chinese Journal of Applied Mechanics

基　　金：国家自然科学基金项目(50775181);航空科学基金(2012ZB53019);西北工业大学基础研究基金(NPU-FFR-JC20110237)

摘　　要：由于全尺寸机翼有限元模型太过复杂,不能用于大型客机翼吊发动机振动载荷的传递特性研究,本文提出了一个全新的机翼双梁动力学模型概念。基于机翼双梁模型的主要模态对其结构刚度不确定参数的灵敏度分析,选取翼梁及翼肋的水平、垂直、扭转刚度参数作为有效设计变量对双梁模型进行了动力学修正,使其与全尺寸机翼有限元参考模型前6阶模态频率的最大误差小于11.11%,大大提升了机翼双梁模型的动力符合性;集成建立了大型客机"吊架-机翼-机身"全机动力有限元模型,并计算了巡航状态下发动机振动载荷经机翼传递到机身各框段的动载荷分布特性。分析结果表明:机翼双梁模型较好地满足了发动机振动载荷传递及振动传递路径分析研究需求,为民机舱内声学预计及发动机隔振安装设计提供了基础数据。In order to investigate the characteristics of vibration load at each frame along airframe transmitted from the engine vibration though the wing structure,a new double-beam dynamical model with 28 ribs of airliner’s wing is presented in this paper.According to the results of the sensitivity analysis for unidentified parameters of the original double-beam model,the effective structural design variables,such as the bending stiffness,torsion stiffness of wing beams and ribs are chosen.Through modifying structural parameters of key wing ribs,the double-beam model’s dynamical characteristic has been improved,in which the maximum error in first six modal frequencies between the double-beam model and a all-size wing FEM model in Ref.[8] is lower than 11.11%.Then a half-full dynamical model with the Pylon-Wing-Airframe of airliner is built,and the vibration load at each frame along airframe transmitted from engine vibration through Mounting-Pylon-Wing is calculated based on it.The acceleration distribution along airframe at main engine feature frequencies under cruise condition is obtained.These results prove that the double-beam dynamical model is better to meet the research needs for the airframe vibration calculation and transmission path analysis of engine vibration,and provides the technical preparation for vibration reduction & isolated mounting system design of wing and pylon structures.

关 键 词：机翼双梁模型 灵敏度分析 动力学修改 振动载荷传递 

分 类 号：V214.3[航空宇航科学与技术—航空宇航推进理论与工程]