大型运输机复杂运动结构随动加载疲劳试验技术  

Large transport aircraft lift-rising structure fatigue test with follow-up load method

作　　者：贺谦[1] 夏峰[1] 张革命[1] 宋鹏飞[1] He Qian;Xia Feng;Zhang Geming;Song Pengfei(Aircraft Strength Research Institute of China.Xi'an 710065,China)

机构地区：[1]中国飞机强度研究所八室,西安

出　　处：《飞行器强度研究》2023年第1期16-23,共8页Aircraft Strength Research

摘　　要：针对某大型运输机襟缝翼结构多维运动特点以及翼面偏转过程同步加载、载荷方向实时跟随等严格的加载要求,进行大型飞机复杂运动结构疲劳试验技术研究。从空间复杂运动翼面载荷精准施加、多系统多参量交互协同控制、复杂耦合试验系统失效保护等三个方面,形成一种大型运输机复杂运动结构随动加载疲劳试验技术。工程应用结果表明,该技术在加载精度及系统安全保护实时性、同步性方面均满足验证评估要求,确保襟缝翼结构寿命评估的准确性和试验运行的可靠性。A structure fatigue life verification method for large aircraft lift-rising components is presented considering spacial complex motion flap and the real-time direction of the load.A spacial motion aircraft lift-rising structure life verification method with coupled multiparameter is established based on accurate load of spacial complex motion flap,multisystem and multiparameter cooperative control and complicated system security protection and the method is validated by a large transport aircraft flap fatigue test.The result shows that the method meets the requirements of flap fatigue life verification in load accuracyandsystemoperation securityprotection.

关 键 词：大型运输机随动加载:疲劳试验 空间轨迹模拟:多参量协同 

分 类 号：TP3[自动化与计算机技术—计算机科学与技术]