摘要
针对全机疲劳试验约束点动态载荷超差导致约束部位结构疲劳失效的问题,研究全机疲劳试验中约束点动态载荷抑制方法。试验分析了多通道协调加载控制激励-响应关系和结构动态载荷响应演化过程,揭示了导致约束点动态不平衡载荷的主要诱因,即控制系统激励-响应相位差与结构动响应的耦合作用。基于黏滞阻尼控制基本原理,提出了弹性阻尼约束方法,并设计了弹性阻尼约束装置。从强度性能、流场分析、瞬态动力学仿真分析等方面说明了方法的可行性,并给出了关键参数的取值范围。在某型飞机全机疲劳试验中开展了应用验证,结果表明弹性阻尼约束可有效降低试验过程中的动态不平衡载荷,可推广至其他型号约束点动态载荷抑制。
To address the problem of structural fatigue failure at the constraint locations caused by dynamic loads ex-ceeding tolerance limits at the constraint points in full-scale aircraft fatigue tests,the main factors contributing to dy-namic load imbalance at the constraint points are studied.The excitation-response characteristics of multi-channel co-ordinated loading control and the structural dynamic load response process are analyzed.It is revealed that the cou-pling between the excitation-response phase difference of the control system and the structural dynamic response is the primary cause of the imbalanced dynamic load at the constraint points.Based on the fundamental principle of damping control,an elastic damping constraint method is proposed,and an elastic damping constraint device is de-signed.The feasibility of the method is demonstrated through structural strength analysis,flow field analysis and tran-sient dynamic simulation,and the optimal ranges for key design parameters are determined.The method and device are validated in the full-scale fatigue test of a certain aircraft model.The results show that the elastic damping con-straint effectively reduces the dynamic load imbalance during testing.The research findings are widely applicable to the full-scale fatigue tests of other aircraft models.
作者
郑建军
王孟孟
牧彬
魏莎
ZHENG Jianjun;WANG Mengmeng;MU Bin;WEI Sha(State Key Laboratory for Strength and Vibration of Mechanical Structures,School of Aerospace,Xi'an Jiaotong University,Xi'an 710049,China;National Key Laboratory of Strength and Structural Integrity,Aircraft Strength Research Institute of China,Xi'an 710065,China;School of Mechanics and Engineering Science,Shanghai University,Shanghai 200444,China)
出处
《航空学报》
北大核心
2025年第21期249-259,共11页
Acta Aeronautica et Astronautica Sinica
基金
国家专项科研(XXZ3-XX21-3)。
关键词
全尺寸飞机结构
疲劳试验
约束点
弹性阻尼约束
动态载荷抑制
full-scale aircraft structure
fatigue test
constraint point
elastic damping constraint
dynamic load suppression
