基于FKM的增材制造钛合金结构疲劳寿命分析方法研究  

RESEARCH ON FATIGUE LIFE ANALYSIS METHOD OF ADDITIVE MANUFACTURING TITANIUM ALLOY STRUCTURE BASED ON FKM STANDARD

作　　者：高焱 金海波[1] 李远杰 谢隋杰 陈晋 王宇[1] GAO Yan;JIN HaiBo;LI YuanJie;XIE SuiJie;CHEN Jin;WANG Yu(Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;CASIC Nanjing Aerospace Sinoequip Co.,Ltd.,Nanjing 210032,China)

机构地区：[1]南京航空航天大学飞行器先进设计技术国防重点学科实验室,南京210016 [2]中国航天科工集团南京航天国器智能装备有限公司,南京210032

出　　处：《机械强度》2024年第4期984-991,共8页Journal of Mechanical Strength

基　　金：航空科学基金项目(20180952007)资助。

摘　　要：基于德国机械工程研究委员会编制的FKM方法,根据已有的试验数据结合有限元仿真计算得到增材制造TA15钛合金材料的相关参数,对增材制造TA15钛合金角盒结构和机加工TA15钛合金角盒结构进行疲劳寿命计算,并对增材制造钛合金角盒结构的疲劳寿命计算结果进行数值分析和试验验证。结果表明,基于FKM方法计算得到的增材制造钛合金角盒结构的疲劳寿命与数值计算结果相比,对数误差在5%以内,与试验寿命相比,对数误差大多在10%以内,基于FKM方法计算得到增材制造钛合金角盒的疲劳寿命高于机加工钛合金角盒结构的疲劳寿命。Based on FKM method prepared by the Geman Mechanical Engineering Committee,the constants of TA15 titanium alloy by additive manufacturing were obtained according to the existing test data and finite element simulation calculation,and the fatigue life of additive manufacturing and machining TA15 titanium alloy angle support were calculated.The fatigue life calculation results of TA15 titanium alloy angle support by additive manufacturing were verified by numerical calculation and tests.The results show that the logarithm error between the fatigue life calculated by FKM method and the numerical calculation result is within 5%,and the logarithm error between the fatigue life calculated by FKM method and the test life is within 10%.The fatigue life of additive manufacturing titanium alloy angle support is higher than that of machining titanium alloy angle support based on FKM method.

关 键 词：增材制造 TA15 钛合金 FKM 方法 数值计算 疲劳试验 疲劳寿命 

分 类 号：V214.9[航空宇航科学与技术—航空宇航推进理论与工程]