摘要
分析了直升机复合材料结构产生损伤的机理,阐述了直升机复合材料结构缺陷及损伤的检测与评估方法,并以某型民用直升机复合材料蜂窝夹层结构修理为实例,讨论了损伤区域的确定、损伤机理的分析及修理原则,给出了修理方案,结果表明通过胶接挖补修补方法修理的结构达到承载能力大于外挂点最大挂载载荷的要求,并且注油30天后无渗油现象,说明用该修理方法能有效地封堵原渗油点,达到了修理的目的,满足某型民用直升机的使用要求。
This paper described the mechanism of damage caused by composite material structure,the inspection and evaluation method of composite material structure default and damage. Also it took X civil helicopter composite material honeycomb structure repair as an example,discussing the definition of damaged area,the analysis of damage mechanism ＆ repairing principle and a repairing scheme was given out. The result indicated that the repaired structure by adding composite material on the surface could meet the requirement that its bearing capacity was greater than the maximum exterior hanging loads,and no leakage occurrences after adding oil 30 days,it meant that repairing by filling material could be effective to plug original leakage point,reaching the goal of repairing ＆meeting the operational requirement for X civil helicopter.
出处
《直升机技术》
2016年第1期58-62,68,共6页
Helicopter Technique
