基于本征正交分解技术的高效气动弹性耦合计算方法  

Efficient aeroelastic coupling computation based on proper orthogonal decomposition technique

作　　者：回庆龙 曹博超 HUI Qinglong;CAO Bochao(Department of Flight Test,Shenyang Aircraft Industry Group Co.,Ltd.,Shenyang 110850,China;Department of Aeronautics and Astronautics,Fudan University,Shanghai 200433,China)

机构地区：[1]中航工业沈阳飞机工业(集团)有限公司试飞站,辽宁沈阳110850 [2]复旦大学航空航天系,上海200433

出　　处：《空气动力学学报》2018年第5期743-748,共6页Acta Aerodynamica Sinica

基　　金：上海市扬帆计划(14YF1400200);上海市晨光计划(13CG01);上海市商用航空发动机领域联合创新计划(AR908.D1RW.002)

摘　　要：将降阶非定常涡格法与结构动力学方程耦合,构造出一种高效的气动弹性计算模型。计算模型中通过引入伪时间步迭代实现了气动与结构计算的紧耦合。另外,通过本征正交分解方法实现了计算模型的降阶。作为方法验证,文中将该方法应用于进行沉浮振荡运动的柔性薄板的气动弹性计算。计算结果表明,仅通过前7个POD模态就可以对涡格法的全模型进行很好的近似,并且该方法在损失很小精度(约1%)的条件下可以实现计算速度的大幅提升(约10倍)。在本文中,降阶模型在POD分析的样本变化范围内和变化范围外都有很好的表现。An efficient aeroelastic computational model is proposed by coupling reduced unsteady vortex lattice method with structural equations of motion.A tight coupling between aerodynamic and structural equations is fulfilled by the introduction of pseudo-time iteration.A model reducing is carried out by proper orthogonal decomposition(POD)technique.This method is validated by the aeroelastic computation on a plunging foil with spanwise flexibility.The results show that the full model of the vortex lattice method can be well approximated by the superposition of only first 7 POD modes.The computational speed of the current problem can be significantly increased(about 10 times)with very little accuracy loss(about 1%).Moreover,in the current validation test,the method performs equally well both inside and outside the parameter variation range of samples for the POD analysis.

关 键 词：气动弹性计算 降阶方法 非定常涡格法 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程]