摘要
根据Ｔ３００／ＱＹ８９１１复合材料的３种典型层合板［０］１６、［９０］２４及［±４５］３Ｓ的试验结果，基于唯象的剩余强度衰减模型和蔡希尔静强度判据，建立单向层合板在任意复杂面内应力作用下的疲劳失效准则。
Fatigue tests are timeconsuming and expensive. Composite laminates can be flexibly designed. Engineers need a way to take full advantage of this flexibility while keeping necessary tests to a minimum. In order to find such a way, we examined existing engineering fatigue failure models and Tsai Hill criterion and tried to extend their applicability. For our purpose, we finally selected residual strength degradation model. Eq.(1) is the well known Tsai Hill criterion for composite laminate failure under static loading. We discussed why X,Y and T in eq.(1) can be replaced by X(σ 1, n), Y(σ 2,n) and T(τ 12 ,n) in order to make it applicable to fatigue failure of composite laminate. Of course, X(σ 1, n), Y(σ 2,n) and T(τ 12 ,n) had to be determined by tests according to residual strength degradation model. Thus we obtained eq.(2), which is similar to eq.(1) but with X,Y and T replaced by X(σ 1, n), Y(σ 2,n) and T(τ 12 ,n) and which is the fatigue failure criterion we sought. Three typical laminates of Chinese T300/QY8911 composite were tested under monotonic tension loading and constant amplitude tension〖CD*2〗tension fatigue loading. They were [0] 16 , [90] 24 and [±45] 3 S . Fig.1 shows the fatigue test data obtained. We obtained Fig.2 by computation involving only monotonic tension test data. We obtained Fig.3 from computation involving fatigue test data in Fig.1 according to the residual strength degradation model. X(σ 1, n) can then be determined from Figs.2(a) and 3(a); Y(σ 2,n) , from Figs.2(b) and 3(b); T(τ 12 ,n) , from Figs.2(c) and 3(c).
出处
《西北工业大学学报》
EI
CAS
CSCD
北大核心
1998年第1期114-118,共5页
Journal of Northwestern Polytechnical University
关键词
复合材料
疲劳
失效准则
composite laminate, fatigue, failure criterion
