替损件设计技术在飞机结构上的应用  

Application of Design Technology of Damageable Substitute to Aircraft Structures

作　　者：徐建新[1] 魏志毅[1] 谭本录 吴朝军[1] 

机构地区：[1]西北工业大学飞行器系,南京航空航天大学飞行器系

出　　处：《南京航空航天大学学报》1998年第3期315-318,共4页Journal of Nanjing University of Aeronautics & Astronautics

摘　　要：详细叙述了替损件的设计思想和设计原则，以及在飞机结构上的应用实例。主梁的疲劳试验和翼身组合体的对比试验结果表明：替损件设计方法可以大大提高结构的抗疲劳品质，并控制裂纹出现的部位，为实现结构长寿命高可靠性的目标，提供了一条成功的途径。The design conception and principle of damageable substitute, and its practical applications in aircraft structures are described in detail. The fatigue tests of main beams and comparative tests of aircraft components demonstrate that the design approach of damageable substitute may greatly improve the quality of anti fatigue of structures, and may control the emerging locations of fatigue cracks. Thus an extremely successful access is supplied to achieve the aims of long life and high reliability of structures.

关 键 词：飞机结构 损伤容限 裂纹 疲劳寿命 替损件 

分 类 号：V215.5[航空宇航科学与技术—航空宇航推进理论与工程]