破片群作用下复合材料结构损伤特性及抢修需求分析  

An Analysis of Damage Characteristics and Emergency Repair Demand of Composite Structural under the Action of Fragment Group

作　　者：郭孝欢 孙法亮 卿华 雍霄驹[1] 夏鑫园 GUO Xiaohuan;SUN Faliang;QING Hua;YONG Xiaoju;XIA Xinyuan(Aviation Maintenance Academy,Air Force Engineering University,Xinyang 464000,Henan,China;Air Defense and Antimissle School,Air Force Engineering University,Xi’an 710038)

机构地区：[1]空军工程大学航空机务士官学校,河南信阳464000 [2]空军工程大学防空反导学院,西安710051

出　　处：《空军工程大学学报》2024年第3期121-126,共6页Journal of Air Force Engineering University

摘　　要：对战斗部破片群作用下复合材料结构损伤规律进行了试验研究。以实际飞机复合材料部件为研究对象,开展了层压板、层压板加筋结构的战斗部地面静爆试验,采用无损检测方法对复合材料在高速冲击下的真实损伤情况进行了检测分析。检测结果表明,遭受单个破片高速冲击的层压板结构的主要损伤形式为破孔+周边分层+表面纤维撕裂,破孔尺寸与弹片尺寸相当,周边分层扩展面积约为破孔面积的1.13~5.00倍。最后,结合修理需求和强度分析结果,提出了修复建议。同样的冲击条件下,层压板结构剩余强度下降比加筋壁板结构的更明显,但从服役的角度看,可能会出现加筋壁板结构剩余承载能力低于极限强度,而层压板结构可采取不修或简单贴补等恢复结构完整性后继续使用的现象。A damage law of composite material structure under the action of warhead fragment group is studied experimentally.Taking the actual aircraft composite components as a research object,the ground static explosion test of the warhead of laminate and laminate reinforced structure is carried out.The real damage of composite materials under high-speed impact is detected and analyzed by nondestructive testing method.The test results show that the main damage forms for laminate structure subjected to high-speed impact of a single fragment serve as a broken hole+peripheral delamination+surface fiber tearing,the size of broken hole is equivalent to the size of fragment’s shrapnel,and the expansion area of peripheral delamination is 1.13~5.00 times larger than that of the broken hole.Finally,the repair suggestions in combination with the repair demand and strength analysis results are put forward.Under the same impact conditions,the residual strength of the laminate structure decreases more obviously than that of the stiff-ened composite structure,but,form the point of service,the residual carrying capacity of the stiffened composite structure may be lower than the ultimate strength,and the laminate structure can be used with-out repair or simply repair after the structural integrity is restored.

关 键 词：破片群 复合材料 损伤特性 抢修 

分 类 号：V214.8[航空宇航科学与技术—航空宇航推进理论与工程]