变刚度复合材料平板与开孔板屈曲性能试验验证与数值仿真

张雅会; 陈普会; 孔斌

doi:10.13801/j.cnki.fhclxb.20220513.001

变刚度复合材料平板与开孔板屈曲性能试验验证与数值仿真

doi: 10.13801/j.cnki.fhclxb.20220513.001

张雅会¹,
陈普会^1, ,,
孔斌^{1, 2}

1.
南京航空航天大学　机械结构力学及控制国家重点实验室，南京 210016
2.
中国航空工业集团公司成都飞机设计研究所，成都 610091

详细信息

通讯作者:
陈普会，博士，教授，博士生导师，研究方向为复合材料结构设计　E-mail: phchen@nuaa.edu.cn

中图分类号: TB332
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- 被引次数: 0
出版历程
- 收稿日期: 2022-04-19
- 修回日期: 2022-04-25
- 录用日期: 2022-05-03
- 网络出版日期: 2022-05-16
- 刊出日期: 2023-04-15

Experimental verification and numerical simulation of buckling behavior of variable stiffness composite plates and open-hole plates

ZHANG Yahui¹,
CHEN Puhui^{1
, ,},
KONG Bin^{1, 2}

1.
State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610091, China

摘要

摘要: 为验证基于丝束曲线铺放的变刚度设计在改善典型航空结构屈曲性能中的应用潜力，设计并制造了变刚度复合材料平板和开孔板试件。通过应变片和非接触式三维光学测量系统，全面地测量了试件受单轴压缩载荷过程中的面外位移和载荷方向应变。试验结果表明：变刚度平板和开孔板较同构型直线铺层试件屈曲载荷分别提升53.4%和46.6%；试件力学响应相似，均为线性加载至屈曲载荷后刚度大幅折减，变刚度试件后屈曲阶段呈近似线性，而直线铺层试件则连续变化。根据试验方案细化了数值模型，屈曲载荷、面外位移及应变的计算结果与试验结果基本吻合。在此基础上，提取了数值模型中的刚度分布和加载截面载荷分布，阐明了变刚度设计的抗屈曲机制。对于本文试件，采用变刚度设计还可显著提高破坏载荷，并降低侧边载荷，缓解应力集中。
- 变刚度复合材料 /
- 层压板 /
- 开孔层压板 /
- 屈曲 /
- 数值仿真
Abstract: To verify the application potential of the variable stiffness design based on tow curve laying in improving the buckling behavior of typical aerospace structures, variable stiffness composite plates and open-hole plates were designed and manufactured. Through the strain gauge and the non-contact 3D optical measurement system, the out-of-plane displacement and load direction strain of the specimens under uniaxial compressive load were comprehensively measured. The experimental results show that the buckling loads of the variable stiffness plates and open-hole plates are increased by 53.4% and 46.6%, respectively, compared with the same configuration of the linear lay-up specimens; The mechanical responses of the specimens are similar, the stiffness is greatly reduced after linear loading to the buckling load, and the post-buckling stage of the variable stiffness specimens is approximately linear, while the linear lay-up specimens vary continuously. The numerical model was refined according to the experimental scheme, and the calculated results of buckling load, out-of-plane displacement and strain are basically consistent with the experimental results. On this basis, the stiffness distribution and load distribution of load section in the numerical models were extracted, and the anti-buckling mechanism of the variable stiffness design was clarified. For the specimens in this paper, the variable stiffness design can also significantly increase the failure load, reduce the side load and relieve the stress concentration.
- variable stiffness composite /
- laminate /
- open-hole laminate /
- buckling /
- numerical simulation

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图 1 变刚度复合材料试件丝束路径定义方法

Figure 1. Method of defining the path of the tow of the variable stiffness composite specimens

T₀—Angle between the tangent line of the reference path at the origin and the positive direction of the x-axis; T₁—Angle between the tangent line of the reference path at the boundary on both sides and the positive direction of the x-axis; T(x_i)—Angle between the tangent line at the coordinate x_i and the positive direction of the x-axis

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图 2 自动丝束铺放设备

Figure 2. Automatic tow laying equipment

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图 3 丝束最小曲率半径R工艺试验结果

Figure 3. Process experimental results of tow’s minimum curvature radius R

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图 4 平移导致的丝束间空隙与重叠区域

Figure 4. Gap and overlap area between tows due to translation

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图 5 变刚度开孔试件构型与标准尺寸

Figure 5. Configuration and standard dimensions of variable stiffness specimen with a hole

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图 6 丝束角度离散化(<45|80>)

Figure 6. Discretization of the curvilinear tow angle (<45|80>)

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图 7 侧边支持夹具

Figure 7. Side support fixture

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图 8 试件应变片布置方案与散斑制作方法

Figure 8. Strain gauge arrangement scheme and speckle fabrication method of test pieces

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图 9 变刚度复合材料压缩试验

Figure 9. Compression experiment of variable stiffness composites

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图 10 T700-12 K/UA2433变刚度复合材料平板和开孔板试件载荷-压缩位移曲线

Figure 10. Load-compression displacement curves of the T700-12 K/UA2433 variable stiffness composite plate and open-hole plate specimens

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图 11 T700-12 K/UA2433变刚度复合材料平板与开孔板试件PB-1 ((a)~(c))与KB-1 ((d)~(f))面外位移光测结果

Figure 11. Optical measurement results of out-of-plane displacement of the T700-12 K/UA2433 variable stiffness composite plate and open-hole plate specimens PB-1 ((a)-(c)) and KB-1 ((d)-(f))

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图 12 变刚度复合材料开孔板数值模型网格及边界条件

Figure 12. Mesh and boundary conditions of numerical model of variable stiffness composite open-hole plates

U1, U3, U2—Displacements in the x, y, and z directions, respectively

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图 13 T700-12 K/UA2433变刚度复合材料平板和开孔板屈曲载荷试验结果与数值计算结果对比

Figure 13. Comparison of experimental and numerical results of buckling load of the T700-12 K/UA2433 variable stiffness composite plates and open-hole plates

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图 14 T700-12 K/UA2433变刚度复合材料平板和开孔板面外位移试验与数值计算结果：(a) PB中心位置；(b) KB的1^#应变片及1^#和2^#应变片中间位置

Figure 14. Experimental and numerical results of out-of-plane displacement of the T700-12 K/UA2433 variable stiffness composite plates and open-hole plates: (a) Central position of the PB; (b) Position of strain gauge 1^# and the middle of 1^# and 2^# of KB

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图 15 T700-12 K/UA2433变刚度复合材料平板和开孔板应变试验与数值计算结果：(a) PB中心位置(1^#和2^#应变片)；(b) KB的1^#和11^#应变测点处

Figure 15. Experimental and numerical results of strain of the T700-12 K/UA2433 variable stiffness composite plates and open-hole plates: (a) Central position of the PB (1^# and 11^# strain gauges); (b) 1^# and 11^# strain gauges of KB

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图 16 T700-12 K/UA2433复合材料平板和开孔板试件后屈曲阶段应变分布光测与数值计算结果对比

Figure 16. Comparison between optical measurement and numerical results of strain distribution of the T700-12 K/UA2433 composite plate and open-hole plate secimens in post-buckling stage

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图 17 T700-12 K/UA2433复合材料平板试件加载方向面内刚度分布

Figure 17. In plane stiffness distribution of the T700-12 K/UA2433 composite plate specimens in loading direction

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图 18 T700-12 K/UA2433复合材料平板和开孔板试件数值模型加载方向截面力分布(50 kN)

Figure 18. Section force distribution in loading direction of the T700-12 K/UA2433 composite plate and open-hole plate specimens numerical models (50 kN)

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表 1 T700-12 K/UA2433碳纤维增强环氧树脂基预浸料工程弹性常数

Table 1. Engineering elastic constants of T700-12 K/UA2433 carbon fiber reinforced epoxy prepreg

E₁/GPa	E₂/GPa	ν₁₂	G₁₂/MPa	G₁₃/MPa	G₂₃/MPa
110	8	0.3	4000	4000	2818
Notes: E₁—Longitudinal elastic modulus; E₂—Transverse elastic modulus; ν₁₂—In-plane Poisson's ratio; G₁₂, G₁₃—In-plane shear modulus; G₂₃—Transverse shear modulus.

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表 2 试件编号与铺层

Table 2. Number and lay-up of specimens

Specimen No.	Lay-up
PA-1-3	[±45]_6s
KA-1-3	[±45]_6s
PB-1-3	[±45/(±<75 \|85>)₂/ ±<65 \|85>/±<65 \|80>/±<0 \|10>]_s
KB-1-3	[±45/(±<75 \|85>)₂/ ±<65 \|85>/±<65 \|80>/±<0 \|10>]_s
Notes: P and K—Panel and open-hole panel specimens; A and B —Used to characterize the two types of lay-ups; 1-3—Number of each piece in each class of specimens.

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表 3 T700-12 K/UA2433变刚度复合材料平板和开孔板屈曲载荷试验与数值分析结果

Table 3. Experimental and numerical results of buckling loads of the T700-12 K/UA2433 variable stiffness composite plates and open-hole plates

Specimen No.	Buckling load/kN
Specimen No.	Experimental result	Average value	Numerical result	Deviation
PA-1	63.9	63.8	56.4	−7.4
PA-2	63.8
PA-3	63.9
PB-1	99.3	97.9	99.9	+2.0
PB-2	92.1
PB-3	102.4
KA-1	60.1	61.1	55.1	−6.0
KA-2	61.2
KA-3	61.9
KB-1	95.3	89.6	92.0	+2.4
KB-2	85.6
KB-3	88.0

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