T800碳纤维增强复合材料加筋壁板压缩稳定性试验及工程计算方法验证  

Compression Stability Test and Engineering Calculation Methods Verification of T800 Carbon Fiber Reinforced Composite Stiffened Panels

作　　者：吕毅[1] 张伟[2] 赵慧[1] 

机构地区：[1]西安航空学院飞行器学院,西安710077 [2]西北工业大学无人机特种技术重点实验室,西安710065

出　　处：《航空工程进展》2017年第3期268-276,共9页Advances in Aeronautical Science and Engineering

基　　金：陕西省自然科学基金(2016JQ1043);陕西省教育厅科研计划项目(16JK1396);西安航空学院校级科研基金(2016KY1101)

摘　　要：国内对T800碳纤维复合材料结构的研究刚刚起步,需要对其加筋壁板的稳定性进行系统地研究。通过改变蒙皮厚度、筋条间距、筋条几何参数等设计8种构型的试验件,进行压缩稳定性试验;考虑侧边边界条件及蒙皮有效宽度的影响,对两种常用的压缩屈曲载荷工程计算方法进行验证。结果表明:在相同筋条面积下,筋条惯性矩提高屈曲载荷增大,加筋壁板的破坏载荷主要取决于壁板的横截面积;蒙皮厚度和筋条间距对屈曲载荷的影响大于对破坏载荷的影响;对于薄蒙皮,当侧边简支且蒙皮有效宽度b=D-b2/2时,计算值与试验值最为接近;对于厚蒙皮,当侧边简支且蒙皮有效宽度b=D时,计算值与试验值最为接近。The research on the structure of T800 carbon fiber composite has just started in our country, so it is necessary to make a systematic study on the stability of stiffened panel with T800 carbon fiber reinforced composite. The test articles of 8 configurations are designed by varying the skin thickness 9 stiffener spacing, stiffener geometric parameters, and the compression stability tests are carried out. Considering the influence of the lateral boundary condition and the effective width of skin, two commonly used compression buckling load engineering calculation methods are verified. Results show that when the moment of inertia increases the buckling load will increase in the same stiffener area,the failure load of stiffened panels mainly depends on the cross sec-tional area of the panels, and the effect of skin thickness and stiffener spacing on buckling load is greater than that on failure load; For the thin skin, when the lateral simply supported and the effective width of skin is b = D-62/2, the calculated value is closest to the experimental value; For the thick skin, when the lateral simply supported and the effective width of skin is b = Df the calculated value is closest to the experimental value.

关 键 词：T800碳纤维 复合材料 加筋壁板 屈曲 工程计算方法 

分 类 号：V258[一般工业技术—材料科学与工程]