南京航空航天大学学报（英文版）
南京航空航天大學學報（英文版）
남경항공항천대학학보（영문판）
TRANSACTIONS OF NANJING UNIVERSITY OF AERONATICS & ASTRONAUTICS
2004年
4期
263-266
,共4页
多轴疲劳%裂纹扩展%比例加载%非比例加载
多軸疲勞%裂紋擴展%比例加載%非比例加載
다축피로%렬문확전%비례가재%비비례가재
multi-axial fatigue%crack propagation%proportional loading%non-proportional loading
对航空材料LY12CZ进行了多种比例和非比例拉扭双轴加载下的疲劳试验.采用弹塑性有限元方法对缺口孔边的应力应变进行了分析,探讨疲劳裂纹扩展方向与孔边各应力和应变分量之间的关系.比较分析结果与试验数据得出:比例加载下,疲劳裂纹基本上在垂直于最大主应变方向扩展.45°及90°非比例加载下,疲劳裂纹沿着最大剪应变平面扩展.
對航空材料LY12CZ進行瞭多種比例和非比例拉扭雙軸加載下的疲勞試驗.採用彈塑性有限元方法對缺口孔邊的應力應變進行瞭分析,探討疲勞裂紋擴展方嚮與孔邊各應力和應變分量之間的關繫.比較分析結果與試驗數據得齣:比例加載下,疲勞裂紋基本上在垂直于最大主應變方嚮擴展.45°及90°非比例加載下,疲勞裂紋沿著最大剪應變平麵擴展.
대항공재료LY12CZ진행료다충비례화비비례랍뉴쌍축가재하적피로시험.채용탄소성유한원방법대결구공변적응력응변진행료분석,탐토피로렬문확전방향여공변각응력화응변분량지간적관계.비교분석결과여시험수거득출:비례가재하,피로렬문기본상재수직우최대주응변방향확전.45°급90°비비례가재하,피로렬문연착최대전응변평면확전.
Various proportional and nonproportional tension-torsion fatigue tests are conducted on aeronautical material-LY12CZ aluminum alloy. The stress and strain states under tension-torsion loading are analyzed by an elastic-plastic finite element method. The relation between the orientation of crack propagation and each stress and strain component is investigated. Analytical results are compared with experimental data. Results demonstrate that the fatigue cracks tend to be propagated perpendicular to the direction of the largest principle strains under proportional loading, and grow alone one of the maximum shear strain planes under 45° and 90° out-of-phase loadings.
