基于静气弹修正的亚音速大展弦比飞机疲劳载荷计算研究  

Subsonic High-Aspect-Ratio Aircraft Fatigue-Load Calculation and Research Based upon Static-Aeroelastic Correction

作　　者：郭天天 王天 Guo Tiantian;Wang Tian(the Stnacture and Strss Branch of Designing Institiate,AVIC XiOn Industry（Group）Company Ltd,Xi＇an 710089,China)

机构地区：[1]航空工业西飞设计院结构强度所,陕西西安710089

出　　处：《安徽师范大学学报（自然科学版）》2018年第3期238-245,共8页Journal of Anhui Normal University(Natural Science)

基　　金：中国航空工业西安飞机工业(集团)公司设计院项目(2017HKG2112)

摘　　要：本文介绍了一种基于静气弹修正的亚音速大展弦比飞机飞行情况疲劳载荷计算方法,该方法以线弹性变形理论为基础,采用了改进的二元升力线理论计算了翼面的气动力,并在风洞试验数据的基础上计算了刚性飞机压力分布的刚性影响,同时借助于线叠加原理对飞机各部件载荷分布加以确定。通过飞机载荷谱飞行实测数据以验证载荷计算结果,证明本文所使用疲劳载荷计算方法有着相对的高精确度。This paper introduces a kind of method for subsonic high-aspect-ratio aircraft flight-fatigue-load calculation based upon the staic-aeroelastic correction. This method is based on the linear-deformation theory,making use of the improved lifting-line theory to calculate the aerodynamic forces on the surface of the wing,confirming the load distribution of aircraft parts with linear superposition principle on the basis of wind tunnel test data which depends on the stiffness calculation of rigid-body-plane pressure distribution. The results of load calculation are verified by the aircraft load spectrum flight test data,which proves that the calculation of the load is of high accuracy.

关 键 词：静气弹修正 疲劳载荷 飞行实测 

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]