复合材料大展弦比机翼动力学建模与颤振分析  

Dynamic Modeling and Flutter Analysis for High-Aspect-Ratio Composite Wing

作　　者：谢长川[1] 张欣[1] 陈桂彬[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《飞机设计》2004年第2期6-10,共5页Aircraft Design

摘　　要：新一代航空结构广泛采用复合材料 ,对复合材料机翼的气动弹性工程化建模和分析是飞机设计的重要任务。应用气动弹性分析理论和方法 ,对复合材料大展弦比机翼进行了结构有限元建模、模型修正、固有振动特性计算、部件发散与颤振工程分析。本文使用MSC/NASTRAN软件 ,在复合材料大展弦比机翼的初步静力分析模型基础上 ,依据结构图纸、相关试验结果反复修改得到合理的机翼结构动力学有限元模型 ,固有振动计算中采用动力减缩方法消除局部模态并提高计算精度 ,采用亚音速偶极子格网法求解非定常气动力 。For the broad usage of composite in new aviation structures, the engineering aeroelastic modeling and analysis of composite wing are important aspects in aircraft design. By using an aeroelasticity theory and method, structure modeling with FEM, model correction, natural vibration calculation, divergence and flutter analysis were done. Based on the structure drawing and related test results, the static analysis model was modified iteratively to get a rational dynamic model. Using MSC/NASTRAN, the dynamic reduction method was applied to avoid local modes and promote calculation accuracy. The divergence and flutter analysis for a composite wing were done in the evaluation of unsteady aerodynamics by subsonic double lattice method.

关 键 词：机翼 气动弹性 航空结构 颤振分析 非定常气动力 展弦比 飞机设计 发散 NASTRAN软件 分析理论 

分 类 号：V211[航空宇航科学与技术—航空宇航推进理论与工程] V224