摘要
介绍了 70 5 0 - T745 2航空铝合金板开缝衬套冷挤压孔结构件的潮湿空气随机载荷谱腐蚀疲劳寿命的试验测定。用威布尔分布给出了置信度和可靠度均为 95 %时的安全寿命 N[95 /95 ]。
An experimental results of corrosion fatigue life with the structure samples of cold extruded hole of aluminum alloy 7050-T7452 was presented.The safety life N 95/95 based on the two parameters Weibull distribution was provided.The result can be used to the strengthening of aircraft structure reliability in moist environment.
出处
《机械科学与技术》
CSCD
北大核心
2000年第2期299-300,共2页
Mechanical Science and Technology for Aerospace Engineering
