航空工程进展
航空工程進展
항공공정진전
ADVANCES IN AERONAUTICAL SCIENCE AND ENGINEERING
2014年
4期
534-540
,共7页
层合板接头%内聚力模型%分层损伤%强度分析%拧紧力矩
層閤闆接頭%內聚力模型%分層損傷%彊度分析%擰緊力矩
층합판접두%내취력모형%분층손상%강도분석%녕긴력구
laminates joints%cohesive zone model%delamination damage%strength analysis%tightening torque
针对传统复合材料损伤分析方法未考虑界面层的损伤问题，基于三维累积损伤分析方法和内聚力模型方法，建立一套能够综合考虑面内损伤和层间损伤的复合材料螺栓连接数值分析模型。通过对两种典型复合材料单钉接头进行强度分析，表明该计算方法比传统有限元方法具有更高的精度。基于该模型，对接头层合板的分层扩展以及拧紧力矩对接头强度和分层扩展的影响进行研究。结果表明：分层扩展方向和层合板断裂方向是一致的；拧紧力矩对连接强度有明显提高作用，并且对孔边分层扩展有抑制作用。
針對傳統複閤材料損傷分析方法未攷慮界麵層的損傷問題，基于三維纍積損傷分析方法和內聚力模型方法，建立一套能夠綜閤攷慮麵內損傷和層間損傷的複閤材料螺栓連接數值分析模型。通過對兩種典型複閤材料單釘接頭進行彊度分析，錶明該計算方法比傳統有限元方法具有更高的精度。基于該模型，對接頭層閤闆的分層擴展以及擰緊力矩對接頭彊度和分層擴展的影響進行研究。結果錶明：分層擴展方嚮和層閤闆斷裂方嚮是一緻的；擰緊力矩對連接彊度有明顯提高作用，併且對孔邊分層擴展有抑製作用。
침대전통복합재료손상분석방법미고필계면층적손상문제，기우삼유루적손상분석방법화내취력모형방법，건립일투능구종합고필면내손상화층간손상적복합재료라전련접수치분석모형。통과대량충전형복합재료단정접두진행강도분석，표명해계산방법비전통유한원방법구유경고적정도。기우해모형，대접두층합판적분층확전이급녕긴력구대접두강도화분층확전적영향진행연구。결과표명：분층확전방향화층합판단렬방향시일치적；녕긴력구대련접강도유명현제고작용，병차대공변분층확전유억제작용。
Countered at the traditional damage analysis of composite without considering the interlaminar failure , based on the three‐dimensional progressive damage analysis and cohesive zone model method ,a new progressive damage model capable of numerically simulating the behavior of bolted composite joints comprehensively consid‐ering composite layer and interlaminar failure is developed .Through the strength analysis of two typical com‐posite single fastener joints ,it shows that the results by new model better agree with the experiments than by the traditional FEM progressive damage model .By this model ,a study of the delamination propagation of the composite joints and the effect of tightening torque on the strength of composite joints and delamination propa‐gation is performed .It is found that the direction of delamination propagation is the same with the orientation of fracture .The tightening torque increases the strength of composite joints obviously and can suppress the delami‐nation propagation at hole in composite joint .
