【摘要】：復(fù)合材料機(jī)械連接件的疲勞問(wèn)題在飛機(jī)結(jié)構(gòu)設(shè)計(jì)中愈顯突出。以復(fù)合材料層合板疲勞中剛度退化模型為基礎(chǔ),分析了復(fù)合材料單釘連接件在疲勞過(guò)程中細(xì)觀機(jī)理,建立了復(fù)合材料單釘連接剩余強(qiáng)度預(yù)測(cè)公式;并開(kāi)展了CCF300/BA9916-ⅡS復(fù)合材料單釘連接疲勞試驗(yàn)。結(jié)果表明,公式預(yù)測(cè)結(jié)果與試驗(yàn)結(jié)果取得較好的吻合。
[Abstract]:The fatigue problem of composite mechanical connectors is becoming more and more prominent in aircraft structure design. Based on the stiffness degradation model of composite laminated plate during fatigue, the meso-mechanism of composite single nail joint during fatigue is analyzed, and the prediction formula of residual strength of composite single nail connection is established. The fatigue test of single nail joint of CCF300/BA9916- 鈪，

本文編號(hào)：2292435