摘要
腐蚀是飞机结构损伤的主要形式之一,严重影响着飞机的结构完整性、可靠性和飞行安全性。某型退役海军飞机曾长期在高温、高湿、高盐雾的沿海机场服役,选取并分解该飞机不参与受力的进气道蒙皮构件,加工制作成标准疲劳试件,通过试验得出剩余寿命。建立相应的疲劳寿命可靠性模型,运用Monte Carlo方法仿真计算可靠性寿命,并将计算结果与试验结果进行比较,初步验证可靠性理论模型的正确性。研究结果表明,该可靠性方法可以应用于飞机结构寿命评估。
Corrosion is the main reason for the aircraft structure damage which has the serious influ- ence on the aircraft structure integrity, reliability and safety. A certain type retired navy aircraft was used to operate in the maritime airport with high temperature, high humidity and an enormous quan- tity of salt fog, the air inlet duct skin element without stress was selected and disassembled and man- ufactured into standard fatigue sample, the remaining life was achieved by experiments. The corre- sponding fatigue life reliability model was established, and the reliability life was simulated and cal- culated by the Monte Carlo method. Compare the calculated results to the test results to demonstrate the validity of the reliability theory model primarily. The results suggested that this reliability method can be used for aircraft structure life evaluation.
出处
《直升机技术》
2013年第3期29-32,共4页
Helicopter Technique
关键词
飞机结构
可靠性
腐蚀
疲劳寿命
aircraft structure
reliability
corrosion
fatigue life
