摘要
列举了飞机薄壁结构紧固件损伤失效故障的典型实例,简要分析了其失效特点与危害性。针对某型飞机机翼前缘襟翼单面连接结构紧固件松动、脱落的故障问题,提出了3种改进方案,并采用拉-拉疲劳试验与振动疲劳试验方法对改进前后的紧固件进行了对比试验。为模拟紧固件在振动疲劳载荷作用下的失效模式与失效过程,研制出了冲击振动试验台;初步建立了飞机结构紧固件振动疲劳试验方法。结果表明,在振动疲劳载荷与传统疲劳载荷作用下飞机结构紧固件的失效模式、损伤机理及寿命分布规律有显著差别。依据试验结果,给出了某型飞机机翼前缘襟翼单面连接结构改进的首选和备选方案。
A typical example of the damage failure of the thin-wall structure fasteners on aircraft was enumerated. The failure characteristics and its harmfulness of the thin-wall structure fasteners on aircraft were analyzed briefly. According to the fasteners loose and fall off failure problem of one sided connection structure of the leading edge of the wing on a certain aircraft, three improved design methods were put forward. And these fasteners with and without improved were experimental comparison verifyed by the tension-tension fatigue and the vibration endurance test methods. The impact vibrationn test device was developed to simulation or representation the failure mode and failure course of fasteners during vibration fatigue loading. A vibration fatigue test method on the thin-wall structure fasteners on aircraft was initially established. The results showed that there is essential difference on failure mode, damage mechanism, wreck destroy break appearance and pattern distributions of fatigue life ~ff the thin-wall structure fasteners between the classical fatigue loading and the vibration fatigue loading. Based on the test results, the preferred and alternative improved design methods on the fasteners of one sided connection structure of the leading edge of the wing on a certain aircraft were provided.
出处
《机械强度》
CAS
CSCD
北大核心
2015年第1期52-57,共6页
Journal of Mechanical Strength
关键词
飞机
薄壁结构
紧固件
失效模式
振动疲劳试验
疲劳寿命
Aircraft
Thin-wall structure
Fastener
Failure mode
Vibration fatigue test
Fatigue life