冲击位置对复合材料加筋板冲击后压缩行为影响试验

任涛; 彭昂; 吴大可; 陆方舟; 蔡登安; 周光明

doi:10.13801/j.cnki.fhclxb.20210328.001

冲击位置对复合材料加筋板冲击后压缩行为影响试验

doi: 10.13801/j.cnki.fhclxb.20210328.001

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

基金项目: 国家自然科学基金(52005256)；江苏省基础研究计划(自然科学基金)(BK20190394)；江苏省博士后科研资助计划项目(2020Z437)；中央高校基本科研业务费专项资金(NS2019001)；机械结构力学及控制国家重点实验室开放课题(MCMS-E-0220Y02)；南京航空航天大学研究生创新基地(实验室)开放基金(kfjj20200104)；江苏高校优势学科建设工程资助项目(PAPD)

详细信息

通讯作者:
周光明，博士，教授，博士生导师，研究方向为先进复合材料结构设计及工程问题的计算机建模　E-mail：zhougm@nuaa.edu.cn

中图分类号: TB332
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出版历程
- 收稿日期: 2021-02-08
- 修回日期: 2021-03-23
- 录用日期: 2021-03-24
- 网络出版日期: 2021-03-29
- 刊出日期: 2022-02-01

Experimental study on the influence of impact positions on compression-after-impact behavior of composite stiffened panels

State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

摘要

摘要: 对低速冲击 (LVI)载荷下不同冲击位置对T型复合材料加筋板损伤容限的影响进行了试验研究。选取了2个典型冲击位置，即：两筋间蒙皮和筋条长桁边缘，引入目视可检冲击损伤(VID)。借助目视及无损检测手段观察到不同冲击位置处的损伤存在显著差异。相比于蒙皮冲击，长桁边缘冲击处的损伤形式更复杂，表现为：纤维断裂、基体开裂、分层、层剥离及界面脱粘。分别对完好、蒙皮冲击和长桁冲击试件进行冲击后压缩试验(CAI)。结果表明：蒙皮冲击件与完好件失效过程极为相似，由于试验夹具刀口的存在，限制了加筋板的变形，诱发了损伤起始，导致最终的结构破坏；而长桁冲击件展示出截然不同的失效机制，损伤从冲击位置沿试件横向扩展，促使结构整体失效的提前发生，显著降低了加筋板的剩余压缩强度。此外，引入数字图像相关技术(DIC)对压缩过程中试件的变形进行监测，并与传统的接触式测量结果进行对比，验证了该测试方法应用于材料力学性能测试的可行性与优越性。
- 复合材料加筋板 /
- 低速冲击 /
- 失效机制 /
- 损伤形态 /
- 数字图像相关技术
Abstract: The effect of impact positions on the damage tolerance of T-stiffened composite panels was investigated by experimental methods. Low velocity impact (LVI) was carried out at two typical locations, namely the center of skin between two stiffeners and the stiffener flange tip of the panels, to introduce visible impact damage (VID). With the help of visual inspection and nondestructive detection, obvious differences in damage morphology from different impact positions were observed. Compared with the skin impact, the damage types induced by the flange tip impact were more complicated, including fiber fracture, matrix cracks, delamination, ply splitting and interface debonding. Compression-after-impact (CAI) tests were performed on the intact, skin-impacted and flange-impacted stiffened panels respectively. The experimental results show that the deformation of skin-impacted panels is restricted due to blade supports, inducing the damage initiation and causing ultimate destruction, which is extremely similar to intact panels. For the flange tip impact, whilst, damage propagation is along the transverse direction from the impact location, which is entirely different from skin impact in the damage scenario, promoting the structural failure and reducing significantly the residual compressive strength. Additionally, the digital image correlation (DIC) was used to monitor the deformation of the specimens during compression and compared with the results of contact measurement, which verified the feasibility and superiority of the test method applied to the mechanical properties of materials.
- stiffened composite panel /
- low velocity impact /
- failure mechanism /
- damage morphology /
- digital image correlation

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图 1 复合材料T型加筋板构型

Figure 1. Configuration of T-stiffened composite panel

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图 2 筋条横截面

Figure 2. Cross section of the stiffener

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图 3 落锤式冲击试验装置

Figure 3. Drop-weight impact test instrument

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图 4 加筋板的冲击位置

Figure 4. Impact location of stiffened panels

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图 5 试验件夹持方式

Figure 5. Clamping method of specimen

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图 6 复合材料加筋板完好件应变片分布和编号

Figure 6. Strain gauges distributions and numbers of intact composite stiffened panels

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图 7 位移计分布和编号

Figure 7. Displacement sensors distributions and numbers

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图 8 复合材料加筋板试件表面散斑

Figure 8. Speckles on the surface of the composite stiffened panel specimen

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图 9 DIC在轴压试验中的应用

Figure 9. Application of DIC in axial compression test

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图 10 组B(在两筋间蒙皮中心处引入冲击损伤)的冲击损伤

Figure 10. Impact damage of group B (Introduce impact damage at the center of skin between two stiffeners)

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图 11 复合材料加筋板超声C扫图像

Figure 11. Ultrasound C scan images of composite stiffened panels

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图 12 组C(在筋条长桁边缘处引入冲击损伤)的冲击损伤

Figure 12. Impact damage of group C (Introduce impact damage at the stiffener flange tip)

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图 13 DIC与位移计测得的复合材料加筋板蒙皮面外位移对比

Figure 13. Comparison of out-of-plane displacements in skin of composite stiffened panels measured by DIC and displacement sensor

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图 14 不同组复合材料加筋板载荷-位移曲线及屈曲波形

Figure 14. Load-displacement curves and deformation patterns of stiffened composite panels from different groups

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图 15 试件A-2关键位置的载荷-应变曲线：(a)蒙皮处；(b)长桁两侧；(c)筋条腹板；(d)腹板下方对应蒙皮位置

Figure 15. Load-strain curves of critical positions of A-2 specimen: (a) On the skin; (b) Both sides of flanges; (c) On the stiffener webs; (d) Corresponding skin positions under the webs

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图 16 试件B-2关键位置的载荷-应变曲线：(a)蒙皮处；(b)长桁两侧；(c)筋条腹板；(d)腹板下方对应蒙皮位置

Figure 16. Load-strain curves of critical positions of B-2 specimen: (a) On the skin; (b) Both sides of flanges; (c) On the stiffener webs; (d) Corresponding skin positions under the webs

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图 17 试件C-1关键位置的载荷-应变曲线：(a)蒙皮处；(b)长桁两侧；(c)筋条腹板；(d)腹板下方对应蒙皮位置

Figure 17. Load-strain curves of critical positions of C-1 specimen: (a) On the skin; (b) Both sides of flanges; (c) On the stiffener webs; (d) Corresponding skin positions under the webs

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图 18 完好的复合材料加筋板破坏模式

Figure 18. Failure mode of intact stiffened composite panel

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图 19 蒙皮受冲击的复合材料加筋板破坏模式

Figure 19. Failure mode of stiffened composite panel with the skin impact damage

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图 20 筋条长桁边缘受冲击的复合材料加筋板破坏模式

Figure 20. Failure mode of stiffened composite panel with the flange tip impact damage

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表 1 碳纤维增强环氧树脂复合材料特性参数

Table 1. Material property parameters of carbon fiber reinforced epoxy resin composite

Material	Property	Value
CCF800/AC531	Longitudinal Young’s modulus E₁₁/GPa	147
	Transverse Young’s modulus E₂₂/GPa	9.25
	In-plane shear modulus G₁₂/GPa	4.40
	Poisson’s ratio ν₁₂	0.33
CF8611/AC531	Longitudinal Young’s modulus E₁₁/GPa	69
	Transverse Young’s modulus E₂₂/GPa	67.9
	In-plane shear modulus G₁₂/GPa	3.97
	Poisson’s ratio ν₁₂	0.047

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表 2 复合材料加筋板冲击损伤的详细测量值

Table 2. Detailed measurements of impact damage of composite stiffened panels

Specimen	Dent depth/mm	Dent length/mm	Dent width/mm
B-1	1.962	14.10	12.84
B-2	1.856	13.74	11.70
B-3	1.752	13.26	11.44
Average value	1.857	13.70	11.99
C-1	2.520	19.20	14.50
C-2	2.384	17.50	14.08
C-3	4.360	19.50	14.50
Average value	3.088	18.73	14.36
Notes: Group B—Impacted at the center of skin between two stiffeners; Group C—Impacted at the stiffener flange tip.

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表 3 复合材料加筋板冲击后压缩试验结果

Table 3. Compression-after-impact test results for stiffened composite panels

Specimen	Type	General buckling of stiffened panels		Ultimate failure of stiffened panels
Specimen	Type	Load/kN	Average load/kN	Load/kN	Average load /kN	Relative change
A-1	Intact	145	142.7	276.230	276.769	−
A-2		143		275.689
A-3		140		278.387
B-1	The skin impact	148	143.7	267.247	271.181	−2.02%
B-2		141		274.750
B-3		142		271.545
C-1	The flange tip impact	142	143.3	205.055	224.775	−18.79%
C-2		145		237.844
C-3		143		231.425

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