改进升力线理论和风洞试验结合的气动弹性修正方法  

Aircraft Aeroelastic Correction Method Based on Combination of Improved Lifting-line Theory and Wind Tunnel Test

作　　者：党西军 郭天天 DANG Xijun;GUO Tiantian(Xi’an Aircraft Industry Group Company Ltd.,Xi’an 710089,China)

机构地区：[1]西安飞机工业集团股份有限公司,陕西西安710089

出　　处：《飞机设计》2021年第3期14-19,共6页Aircraft Design

摘　　要：为了考虑具有大展弦比、弹性翼面结构的飞机翼面结构弹性变形对气动载荷分布的影响。介绍了一种基于亚声速稳态定常流改进升力线理论与风洞试验相结合的大展弦比亚声速飞机的弹性翼面气动力分布载荷修正方法,本方法在飞机翼面载荷设计中,考虑了弹性变形的影响,满足了飞机设计规范中对结构载荷设计的条款要求,对静强度和疲劳设计都有直接影响,对刚度设计和气动力设计优化有重要的反馈评估作用。A modified method for aerodynamic load distribution on the elastic wing surface of a subsonic high aspect ratio aircraft based on the improved lift line theory of subsonic steady flow and wind tunnel test is presented,and the purpose of the design is to consider the influence of the elastic deformation of the wing structure on the aerodynamic load distribution.This method considers the influence of the elastic deformation and meets the requirements of structural load design in the aircraft design specification whch has direct influence on static strength and fatigue design and plays an important role in the feedback evaluation of stiffness design and aerodynamic design optimization.

关 键 词：升力线理论 大展弦比 风洞试验 气动弹性修正 气动载荷分布 

分 类 号：V211.8[航空宇航科学与技术—航空宇航推进理论与工程]