复合材料帽型加筋板等效弯曲刚度

吴菁; 胡明勇; 章向明; 杨少红; 王安稳

doi:10.13801/j.cnki.fhclxb.20211208.001

复合材料帽型加筋板等效弯曲刚度

doi: 10.13801/j.cnki.fhclxb.20211208.001

海军工程大学　基础部，武汉 430033

基金项目: 国家自然科学基金(51479206)；海军工程大学2022年自主研发项目(425317T00G)

详细信息

通讯作者:
胡明勇，博士，教授，硕士生导师，研究方向为船舶结构力学和复合材料力学　E-mail: shuai_humingyong@163.com

中图分类号: TB330.1
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出版历程
- 收稿日期: 2021-10-14
- 修回日期: 2021-11-22
- 录用日期: 2021-11-26
- 网络出版日期: 2021-12-11
- 刊出日期: 2022-12-01

Equivalent bending stiffness of composite hat-stiffened panel

Department of Basic Courses, Naval University of Engineering, Wuhan 430033, China

摘要

摘要: 复合材料船体结构主要由纵向或横向加筋板架构成，复合材料加筋板设计可以近似处理成正交异性板，需要定量计算复合材料加筋板的等效刚度。利用卡氏定理推导了复合材料帽型加筋层合板的纵向和横向弯曲刚度，给出了等效层合板弯曲刚度的解析表达式。通过复合材料帽型加筋层合板纵向和横向三点弯曲试验实测梁的跨中挠度并与等效弯曲刚度对应的解析解比较；用ABAQUS有限元软件计算三点弯曲纵向和横向复合材料帽型加筋梁和四边简支复合材料帽型加筋板中心点的挠度并与等效弯曲刚度对应的解析解比较。结果表明：解析解与数值计算及试验结果对比，吻合较好，验证了等效弯曲刚度解析表达式的正确性，且具有较好的计算精度，可作为复合材料帽型加筋板设计的计算依据。
- 复合材料船体 /
- 帽型加筋板 /
- 等效弯曲刚度 /
- 解析解 /
- 弯曲试验
Abstract: The composite hull is mainly composed of longitudinally or transversely stiffened laminates. The design of composite stiffened laminates can be approximated as an orthogonal anisotropic plate and the equivalent stiffness of stiffened composite plates needs to be calculated quantitatively. The longitudinal and transverse bending stiffness of hat-stiffened panel were derived using the Castigliano's theorem. The analytical expressions for the equivalent bending stiffness were provided. The longitudinal and transverse three-point bending tests of the hat-stiffened laminates were designed to measure the mid-span deflection of the beam and the obtained test data were compared with the analytical solution corresponding to the equivalent bending stiffness. The deflection at the center point of longitudinally and transversely hat-stiffened composite beam in three-point bending and the four-sided simply-supported hat-stiffened composite laminates was calculated by ABAQUS and compared with the analytical solution corresponding to the equivalent bending stiffness. The results show that the analytical solutions are in good agreement with the numerical calculations and the experimental results, which verifies the correctness of the analytical expression of the equivalent bending stiffness. It can be used confidently in the design of the hat-stiffened panel.
- composite hull /
- hat-stiffened panel /
- equivalent bending stiffness /
- analytic solution /
- bending test

HTML全文

图 1 帽型加筋层合板

Figure 1. Hat-stiffened panel

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图 2 帽型加筋层合板典型单元横截面

Figure 2. Representative sectional element of hat-stiffened panel

①-⑥—Elementary component; S—Width of representative unit; a—Foot width; b—Extending width; w_t—Bottom width; w_b—Top width; t_p—Panel thickness; t_c—Side thickness; t_b—Top thickness; l—Side length; h—Hat height

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图 3 受横向弯矩作用的加筋帽单元

Figure 3. Hat-stiffened element under transverse bending

ξ—Natural coordinate; θ—Angle of sides; M_P—Plate bending moment; M_c—Hat bending moment; P—Load; M_y—Total bending moment

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图 4 纵向弯曲帽型加筋板试件截面尺寸

Figure 4. Dimensions of transverse section of longitudinally-bending-test hat-stiffened panel

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图 5 横向弯曲帽型加筋板试件截面尺寸

Figure 5. Dimensions of longitudinal section of transversely-bending-test hat-stiffened panel

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图 6 试验装置

Figure 6. Test device

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图 7 帽型加筋板挠度随载荷变化

Figure 7. Relation between the load and mid-span deflection of hat-stiffened panel

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图 8 帽型加筋板的弯曲变形：(a) 沿纵向(F=2 kN)；(b) 沿横向(F=0.2 kN)

Figure 8. Displacement of hat-stiffened composite laminates: (a) Under longitudinally bending (F=2 kN); (b) Under transversely bending (F=0.2 kN)

U—Displacement; U2—Displacement in y dirction

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图 9 帽型加筋板结构示意图

Figure 9. Geometry of hat-stiffened plate

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图 10 四边简支帽型加筋板最大挠度

Figure 10. Maximum deflection of four-sided simply-supported hat-stiffened composite laminates

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图 11 四边简支帽型加筋板的弯曲变形

Figure 11. Displacement of four-sided simply-supported hat-stiffened composite laminates

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