复合材料层合板钝头体高能量低速冲击响应与损伤特性

邹君; 刘佳鑫; 王计真; 郭亚周; 李玲玲; 冯振宇

复合材料层合板钝头体高能量低速冲击响应与损伤特性

1.
中国民航大学　安全科学与工程学院, 天津 300300
2.
民航航空器适航审定技术重点实验室, 天津 300300
3.
中国飞机强度研究所, 西安 710065

基金项目: 机械结构力学及控制国家重点实验室开放课题 (MCMS-E-0522Y03)；中央高校基金(3122022099)

详细信息

通讯作者:
邹君，博士，讲师，硕士生导师，研究方向为飞行器结构综合设计及强度分析技术　E-mail: jzou@cauc.edu.cn

中图分类号: TB332
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出版历程
- 收稿日期: 2023-08-01
- 修回日期: 2023-09-18
- 录用日期: 2023-09-27
- 网络出版日期: 2023-10-19
- 刊出日期: 2024-06-15

Response and damage characteristics of composite laminates under high-energywide-area blunt impact

1.
College of Safety Science and Engineering, Civil Aviation University of China, Tianjin 300300, China
2.
Key Laboratory of Civil Aircraft Airworthiness Technology, CAAC, Tianjin 300300, China
3.
Aircraft Strength ResearchInstitute of China, Xi’an 710065, China

Funds: Research Fund of State Key Laboratory of Mechanics and Control of Mechanical Structures (MCMS-E-0522Y03)；Fundamental Research Funds for the Central Universities in China (3122022099)

摘要

摘要: 高能量大面积钝物冲击(HEWABI)会导致复合材料飞机结构内部发生严重损伤，但在机身外部几乎目视不可见，从而会对飞机运营安全带来较大的威胁。采用不同形状的刚性冲头和橡胶冲头对层合板进行高能量准静态加载试验，随后建立了基于连续介质损伤力学(CDM)的仿真分析模型。结果表明：建立的仿真分析模型可有效预测在刚性和橡胶冲头下的响应和损伤情况。当载荷达到40 kN时，刚性冲头下的层合板会发生严重的分层损伤；而橡胶冲头在加载过程中发生大变形，降低了层合板的局部应力，直至90 kN时仍未对层合板产生任何损伤。层合板损伤情况受刚性冲头形状影响较大，橡胶冲头形状则几乎无影响。
- 层合板 /
- 高能量大面积钝物冲击 /
- 橡胶冲击 /
- 冲击响应 /
- 损伤特性
Abstract: High-energy wide-area blunt impact (HEWABI) can lead to severe internal damage to the composite aircraft, which is barely visible from the outside of fuselage and cause a significant threat to flight safety. High energy quasi-static loading tests were carried out on the laminates with different shapes of rigid impactors and rubber impactors, then the finite element simulation models based on Continuum Damage Mechanics (CDM) were developed. The results show that the established simulation analysis models can effectively predict the response and damage of the laminated panels under rigid or rubber impactors. When the load reaches 40 kN, severe delamination damages will occur in the laminated panel for the rigid impactors. On the other hand, no damage can be observed at 90 kN for the rubber impactors, which can be attributed to the significant deformation of rubber impactors and the reduced local contact loads. The shape of rigid impactors has great effect on the damage to laminated panels, while the shape of the rubber impactors has almost no impact on the damages.
- laminate /
- high-energy wide-area blunt impact /
- rubber impact /
- impact response /
- damage characteristics

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图 1 冲头形状与尺寸(单位：mm)

Figure 1. Impactor’s shape and dimensions (Unit: mm)

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图 2 试验件及夹具安装示意图

Figure 2. Installation of the laminates and fixture

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图 3 有限元模型

Figure 3. Finite element model

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图 4 刚性冲头的试验和仿真载荷-位移曲线对比

Figure 4. Comparison of experimental and simulated load displacement curves for rigid impactors

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图 5 橡胶冲头的试验和仿真载荷-位移曲线对比

Figure 5. Comparison of experimental and simulated load displacement curves for rubber impactors

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图 6 DE710-T700S层合板形貌

Figure 6. DE710-T700S Laminate profile

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图 7 DE710-T700S层合板冲击后C扫描损伤图

Figure 7. The damage of DE710-T700S laminate under C-Scan

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图 8 DE710-T700S层合板仿真分层损伤累计结果

Figure 8. Simulated cumulative delamination damage results ofDE710-T700S laminate

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图 9 橡胶变形试验结果与仿真结果对比图

Figure 9. The comparison of experiment and simulation results of rubber deformation

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图 10 不同冲头下DE710-T700S层合板位移云图

Figure 10. Displacement contours of the DE710-T700S laminate under different impactors

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图 11 不同冲头下DE710-T700S层合板载荷-位移曲线对比

Figure 11. Comparison of load-displacement curves of DE710-T700S laminated plates under different impactors

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图 12 DE710-T700S层合板内能-位移曲线对比

Figure 12. Comparison of internal energy displacement curves of DE710-T700S laminated plates

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表 1 DE710-T700S单向板材料力学性能参数

Table 1. Mechanical property parameters of DE710-T700S unidirectional plate material

Parameter	Value
ρ/(g·cm⁻³)	1.53
E₁₁/GPa	121
E₂₂/GPa	8.6
E₃₃/GPa	8.6
ν₁₂	0.317
ν₁₃	0.317
ν₂₃	0.5
G₁₂/GPa	3.7
G₁₃/GPa	3.7
G₂₃/GPa	3.7
X_t/MPa	2376
X_c/MPa	1068
Yt/MPa	69
Y_c/MPa	208
S_l/MPa	110
S_t/MPa	110
Notes: E_ii(i=1,2,3)—Elastic modulus in direction i; v_ij(i=1,2; j=2,3)—Poisson's ratio in different directions; G_ij(i=1,2; j=2,3)—Shear modulus in different directions; X_t and X_c—Longitudinal tensile and compressive strengths; Y_t and Y_c—Transverse tensile and compressive strengths; S_l and S_t—Longitudinal and transverse shear strength.

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表 2 DE710-T700S层合板层间性能参数

Table 2. Interface performance parameters of DE710-T700S laminate

Parameter	Value
E/GPa	8.6
$t_{\text{n}}^0$/MPa	26
$t_{\text{s}}^0$/MPa	62
$t_{\text{t}}^0$/MPa	62
G_IC/(J·m⁻²)	771
G_IIC/(J·m⁻²)	3152
G_IIIC/(J·m⁻²)	3152
Notes: E—Elastic modulus of cohesive layer; $t_{\text{n}}^0$($t_{\text{s}}^0$,$t_{\text{t}}^0$)—Interfacial strengths in three main directions; G_IC (G_IIC, G_IIIC)—Critical energy release rates for different types of cracking.

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表 3 Ogden材料参数(N=2)

Table 3. Ogden material parameters (N=2)

i	µ_i/MPa	α_i
1	0.459	3.564
2	3.409	−0.149

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