复合材料翼面壁板轴压稳定性

石经纬; 赵娟; 刘传军; 李东升

doi:10.13801/j.cnki.fhclxb.20190917.003

复合材料翼面壁板轴压稳定性

doi: 10.13801/j.cnki.fhclxb.20190917.003

1.
中国商用飞机有限责任公司　北京民用飞机技术研究中心，北京 102211
2.
北京荣广盛工程管理有限公司，北京 100089

基金项目: 工信部民机专项基金（MJ-2017-F-20）

详细信息

通讯作者:
石经纬，博士，工程师，研究方向为复合材料民机结构有限元分析　E-mail：shijingwei@comac.cc

中图分类号: TB332
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- 被引次数: 0
出版历程
- 收稿日期: 2019-06-27
- 录用日期: 2019-09-09
- 网络出版日期: 2019-09-17
- 刊出日期: 2020-06-15

Stability of composite stiffened panels under compression

1.
Beijing Aeronautical Science & Technology Research Institute of Commercial, Aircraft Corporation of China, LTD., Beijing 102211, China
2.
Beijing ROCOSN Engineering Management CO. LTD., Beijing 100089, China

摘要

摘要: 基于T型长桁铺层数不同的两块复合材料翼面加筋壁板试件SC-1和SC-2，开展轴压稳定性试验研究，并提出一种预测屈曲载荷及最小后屈曲承载能力的工程分析方法，结合有限元特征值屈曲分析方法、有限元弧长法对试件的屈曲载荷、屈曲模态及后屈曲承载能力进行分析。试验结果表明，铺层数较多的试件SC-1的蒙皮局部屈曲应变较高，壁板也具有更高的屈曲载荷。在后屈曲阶段，SC-2加载到试验屈曲载荷的2.4倍未发生材料破坏和长桁蒙皮间脱粘损伤。工程分析方法和特征值屈曲分析能够准确预测壁板的屈曲载荷，最大误差分别为-9.3%和-2.8%，工程分析得到SC-2的最小后屈曲承载能力为试验屈曲载荷的2.09倍。有限元弧长法分析得到两件试件的屈曲载荷误差均小于1%，并具有壁板轴压屈曲模态预测和变形跟踪能力。
- 加筋壁板 /
- 轴压稳定性 /
- 屈曲 /
- 工程分析 /
- 特征值 /
- 弧长法
Abstract: Experiments for compression stability analysis were conducted on composite stiffened panels SC-1 and SC-2 with different T-stringer lay-ups. A proposed engineering method was introduced to predict the buckling load and the least post-buckling carrying capability, and finite element analysis with eigenvalue method and arc-length method were carried out to investigate the bucking load, buckling mode, and post-buckling carrying capability. Experiment results show that SC-1 with more stringer ply-ups possess the higher local bucking strain of skin and the higher buckling load of the panel, and SC-2 can sustain a post-buckling carrying capability of 2.4 times of buckling load without material damage and stringer-skin debonding. The engineering method and eigenvalue method acquire the buckling loads of the panels with errors of -9.3% and -2.8% respectively, and the minimum post-buckling carrying capability of SC-2 is 2.09 times of experimental buckling load by engineering method. The errors of buckling loads by arc-length method are less than 1% for both SC-1 and SC-2, and the buckling modes and distortion are well trailed with load increasing.
- stiffened panels /
- compression stability /
- buckling /
- engineering method /
- eigenvalue /
- arc-length method

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图 1 碳纤维增强树脂（CFRP）复合材料加筋壁板试件

Figure 1. Carbon fiber reinforced polymer(CFRP) stiffened panel specimen

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图 2 CFRP复合材料加筋壁板应变片布置

Figure 2. Strain gauges distribution on CFRP composite stiffened panels

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图 3 CFRP复合材料加筋壁板轴压稳定性试验加载方式

Figure 3. Loading method for compression stability test of CFRP composite stiffened panels

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图 4 CFRP复合材料加筋壁板试件截面尺寸示意图

Figure 4. Schematic diagram of cross-section dimensions of the CFRP composite stiffened panel

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图 5 单块CFRP复合材料蒙皮试验应变曲线

Figure 5. Experimental strain curves on a piece of CFRP composite skin

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图 6 CFRP复合材料蒙皮横截面试验应变曲线

Figure 6. Experimental strain curves on a cross-section of CFRP composite skins

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图 7 CFRP复合材料长桁腹板试验应变曲线

Figure 7. Experimental strain curves on CFRP composite stinger web

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图 8 长桁缘条与蒙皮试验应变曲线

Figure 8. Experimental strain curves on skin and stringer flange

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图 9 CFRP复合材料加筋壁板SC-1的轴压屈曲模态特征值法分析结果

Figure 9. Buckling modes of CFRP composite stiffened panel SC-1 under compression by eigenvalue method

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图 10 CFRP复合材料加筋壁板SC-2的轴压屈曲模态特征值法分析结果

Figure 10. Buckling modes of CFRP composite stiffened panel SC-2 under compression by eigenvalue method

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图 11 CFRP复合材料蒙皮横截面有限元应变曲线弧长法分析结果

Figure 11. Strain curves of CFRP composite skin cross-section by arc-length method

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图 12 CFRP复合材料长桁腹板有限元应变曲线弧长法分析结果

Figure 12. Strain curves of CFRP composite string web by arc-length method

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图 13 CFRP复合材料加筋壁板试件加载端“位移-载荷”及其变化率曲线

Figure 13. Displacement-force and its rate of change curves of loading end of CFRP composite stiffened panel specimen

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图 14 CFRP复合材料加筋壁板试件SC-1面外位移云图

Figure 14. Out-of-plane displacement contours of CFRP composite stiffened panel SC-1

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图 15 CFRP复合材料加筋壁板试件SC-2面外位移云图

Figure 15. Out-of-plane displacement contours of CFRP composite stiffened panel SC-2

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图 16 1.2倍屈曲载荷下CFRP复合材料加筋壁板SC-1轴向应变云图

Figure 16. Axial strain contour of CFRP composite stiffened panel SC-1 under 1.2 times of buckling load

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图 17 2.3倍屈曲载荷下CFRP复合材料加筋壁板SC-2轴向应变云图

Figure 17. Axial strain contour of CFRP composite stiffened panel SC-2 under 2.3 times of buckling load

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图 18 1 150 kN时CFRP复合材料加筋壁板SC-2中间长桁位移曲线及侧向位移云图

Figure 18. Displacement of central stringer and transverse displacement contour of CFRP composite stiffened panel SC-2 at 1 150 kN

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表 1 X850 CFRP复合材料单向带的力学性能

Table 1. Mechanical properties of X850 CFRP composite prepreg

E₁₁/MPa	E₂₂/MPa	G₁₂/MPa	ν₁₂
158 000	9 000	4 140	0.319
Notes: E₁₁—Elastic modulus in fibre direction; E₂₂—Elastic modulus transverse to fibre direction; G₁₂—Shear modulus; ν₁₂—Poisson’s ratio.

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表 2 CFRP复合材料加筋壁板铺层顺序

Table 2. Stacking sequences of CFRP composite stiffened panels

Region	Stacking sequence
Skin	[45/−45/0/45/−45/0/0/90]s
L_left(SC-1)	[−45/45/0/0/0/90/−45/0/45/45/0/−45/90/0]
L_left(SC-2)	[−45/45/0/0/0/90/−45/0/45/90/0]
L_right(SC-1)	[45/−45/0/0/0/90/45/0/−45/−45/0/45/90/0]
L_right(SC-2)	[45/−45/0/0/0/90/45/0/−45/90/0]
Insert plys	[45/−45/0/0]

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表 3 CFRP复合材料加筋壁板轴压屈曲载荷工程方法分析结果

Table 3. Buckling load of CFRP composite stiffened panels under compression by engineering method

Specimen	t_ply,equ/mm	$\eta $	P_b/kN	${\varepsilon _{{\rm{blk}}}}$/10⁻³
SC-1	0.265	0.158	549	−1.188
SC-2	0.252	0.164	453	−1.066
Notes: t_ply,equ—Equivalent ply thickness; P_b—Buckling load; ${\varepsilon _{{\rm{blk}}}}$—Buckling strain; η—Stiffness ratio of a single skin to a whole stiffened wall.

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表 4 CFRP复合材料加筋壁板轴压稳定性特征值分析结果

Table 4. Results of compression stability analysis of CFRP composite stiffened panels by eigenvalue method

Mode	Eigenvalue		Buckling load/kN
Mode	SC-1	SC-2	SC-1	SC-2
1	1.545	1.214	618	486
2	1.547	1.217	619	487
3	1.553	1.265	621	506
4	1.612	1.338	645	535
5	1.668	1.400	667	560
6	1.684	1.403	674	561

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