摘要
目的研究军用飞机高强螺栓在模拟海洋大气环境下的疲劳极限变化。方法采用中性盐雾试验对30CrMnSiA高强螺栓进行预腐蚀试验,试验持续时间为360 h,而后再进行96 hCASS试验。腐蚀后对样品进行疲劳试验,并与未腐蚀的样品进行S-N曲线对比分析,并分析其疲劳断口形貌变化。结果在进行盐雾试验后螺栓发生腐蚀,疲劳极限降低28.4%。结论军用飞机用高强螺栓在模拟海洋大气环境下易发生腐蚀,疲劳极限出现明显降低现象,其主要原因为疲劳试验有效面积减少。
Objective To research the change of fatigue limit of high strength bolt for military airplane exposed to simulated marine atmosphere environment （salt-fog environment）. Methods The high strength bolt was proceed with pre-corrosion test by 360 hours of neutral salt-fog test followed by 96 hours of CASS test. The fatigue test was performed after the corrosion test. The corroded sample was compared with the uncorroded by virtue of the S-N curve and fracture morphologies. Results The bolt was corroded after salt-fog test and the fatigue limit of high strength bolt decreased by 28.4%. Conclusion High strength bolt for military airplane is likely to be corroded in the simulated marine atmosphere environment and its fatigue limit decreases evidently. Its main reason is the reduction of effective fatigue test area due to serious corrosion.
出处
《装备环境工程》
CAS
2017年第3期57-59,共3页
Equipment Environmental Engineering
关键词
高强螺栓
盐雾
疲劳极限
S-N曲线
断口形貌
high strength bolt
salt-fog
fatigue limit
S-N curve
fracture morphology
