摘要
由于现代飞机对安全和轻质提出了更高要求,因此需不断研制高强轻质材料.本文研究了一种超高强钛合金,其拉伸强度达1300 MPa.为了使其应用于飞行器的关键连接结构,需获得该钛合金耳片的拉伸强度计算公式和方法.然而,目前不清楚《飞机设计手册》的耳片拉伸强度计算公式是否适用于该材料,也未知该钛合金耳片的拉伸破坏机理.因此,本文设计了不同钛合金耳片,通过开展不同方向的拉伸破坏试验,得到不同耳片在不同作用方向下的拉伸破坏载荷,验证和修正《飞机设计手册》针对钛合金耳片拉伸强度计算公式,开展钛合金耳片受拉伸下的弹塑性有限元分析,结合试验结果,揭示该钛合金耳片拉伸破坏机制.
In response to increasing demands for enhanced safety and weight reduction in modern aircraft,the development of high-strength,lightweight materials are still highly demanded.This study focuses on an ultra-high-strength titanium alloy with a tensile strength of 1300 MPa,intended for use in critical lug.It is important to determine the tensile strength of the titanium alloy lug for its use in aerospace components.However,the applicability of the tensile strength formulas from the"Aircraft Design Manual"to this material remains uncertain,as does the tensile failure mechanism.Therefore,in this paper we design multiple titanium alloy lug configurations and perform tensile tests to determine the corresponding failure loads.Through the test results,the tensile strength formulas in the"Aircraft Design Manual"for titanium alloy lugs are updated.Combined with elastoplastic finite element analysis and experimental data,the tensile failure mechanism of the titanium alloy lugs is revealed.
作者
秦锋英
李波
龙思雨
吴孟轩
徐武
QIN Fengying;LI Bo;LONG Siyu;WU Mengxuan;XU Wu(AVIC The First Aircraft Institute,Xi′an 710089,Shaanxi,China;School of Aeronautics and Astronautics,Shanghai Jiao Tong University,Shanghai 200240,China)
出处
《力学季刊》
北大核心
2025年第2期349-359,共11页
Chinese Quarterly of Mechanics
基金
国家自然科学基金(12172217)。
关键词
钛合金耳片
拉伸强度
弹塑性有限元分析
破坏机制
titanium alloy lug
tensile strength
elastic-plastic finite element analysis
failure mechanism
