含镍铬合金丝电热层复合材料低速冲击性能试验研究

doi:10.12382/bgxb.2024.0962

摘要/Abstract

摘要：

为开发既具有防/除冰功能又可以满足承载性能要求的电热复合材料,基于定制纤维铺放工艺设计制备3种镍铬合金丝并联间距(6.67mm、4.00mm和2.86mm)的电加热织物及其增强复合材料,在25W功率下,3min内复合材料表面温度最低可达87.2℃。采用落锤冲击试验机、红外热像仪和万能强力试验机测试,并分析复合材料试样在7J下的低速冲击性能、冲击后电热性能和冲击后压缩性能。研究结果表明:引入镍铬合金丝电热层后复合材料冲击吸能至少增加23.6%;电热复合材料在未发生穿孔的情况下,冲击后损伤区域的表面温度仍然可以达到72.4℃以上,冲击后压缩模量和压缩强度保留率分别可达到88.73%和94.97%以上;与玻纤/环氧复合材料相比,随着镍铬合金丝并联间距减小,电热复合材料在冲击后压缩载荷下电热层处分层现象更为显著,这一结果为飞行器防/除冰用电热复合材料兼顾力学性能的设计提供实践意义的指导。

关键词: 复合材料, 定制纤维铺放, 电加热织物, 低速冲击性能, 冲击后电热性能, 冲击后压缩性能

Abstract:

To develop the electrically-heated composites that have both anti-icing/de-icing functionality and meet load-bearing performance requirements,three types of electrically-heated fabrics containing nickel-chromium alloy wires with parallel spacings of 6.67mm,4.00mm and 2.86mm and their reinforced composites are designed and fabricated based on the tailored fiber placement process.The lowest surface temperature of the composites reaches 87.2℃ within three minutes at 25W.The low-velocity impact properties,electro-thermal properties and compression properties of the composites subjected to 7J impact load are tested and analyzed using a drop weight impact tester,an infrared thermal imager,and a universal testing machine.The results indicate that the impact energy absorption of composite with a the nickel-chromium alloy wire electrically-heated layer is increased by at least 23.6%.The surface temperature of the damaged areas in the electrically-heated composites can still reach above 72.4℃ after impact,and the retention rates of post-impact compressive modulus and compressive strength are 88.73% and 94.97%,respectively.Compared to glass fiber/epoxy composites,the decrease in the parallel spacing of nickel-chromium alloy wires results in a more pronounced delamination phenomenon in the electrically-heated layer under post-impact compressive load.These findings provide practical guidance for the design of electrically-heated composites for aircraft anti-icing/de-icing applications,ensuring a balance between mechanical performance and functional requirements.

Key words: composites, tailored fiber placement, electrically-heated fabrics, low-velocity impact property, post-impact electro-thermal property, post-impact compressive property

中图分类号:

TB332

王守涛, 居傲, 郭静娴, 赵长青, 赵晨, 崔艳超, 孙颖, 陈利. 含镍铬合金丝电热层复合材料低速冲击性能试验研究[J]. 兵工学报, 2025, 46(8): 240962-.

WANG Shoutao, JU Ao, GUO Jingxian, ZHAO Changqing, ZHAO Chen, CUI Yanchao, SUN Ying, CHEN Li. Low-velocity Impact Properties of Electrically-heated Composites Containing Nickel-chromium Alloy Wires[J]. Acta Armamentarii, 2025, 46(8): 240962-.

图/表 24

图1 电加热织物

Fig.1 Electrically-heated fabric

表1 试样参数实测值

Table 1 Measured values of sample parameters

试样组	并联间距/mm	厚度/mm	面密度/(kg·m^-2)
EC1	6.67	2.23±0.02	3.702
EC2	4.00	2.23±0.02	3.698
EC3	2.86	2.23±0.02	3.683
GFRP		2.08±0.01	3.575

图2 电热复合材料试样

Fig.2 Electrically-heated composite samples

图3 复合材料电热性能测试

Fig.3 Electrothermal properties of composites

表2 电热复合材料试样升温特性

Table 2 Temperature rise properties of electrically-heated samples

试样组	60s内升温速率/ (℃·s^-1)	最高温度/ ℃	最低温度/ ℃	表面温差/ ℃
EC1	0.803	113.4±2.5	87.2±2.0	26.2±1.8
EC2	0.685	106.1±2.1	94.6±1.6	11.5±0.6
EC3	0.573	97.7±1.2	91.6±1.1	6.1±0.4

图4 试样表面温度-时间曲线

Fig.4 Sample surface temperature-time curves

图5 复合材料低速冲击和冲击后压缩性能测试

Fig.5 Low-velocity impact and CAI tests of composites

图6 典型冲击载荷-时间和能量-时间曲线

Fig.6 Typical impact load-time and energy-time curves

图7 试样典型冲击载荷-时间曲线

Fig.7 Sample typical impact load-time curves

表3 复合材料试样冲击性能测试结果

Table 3 Test impact properties of composite samples

试样组	F₁/N		F_max/N		E_D/J		D_E/mm		D_D/mm
试样组	测试值	变异系数/%	测试值	变异系数/%	测试值	变异系数/%	测试值	变异系数/%	测试值	变异系数/%
EC1	1647	3.05	2040	4.23	5.75	2.87	5.88	1.73	0.67	7.16
EC2	1780	3.23	1993	4.11	5.83	1.29	5.74	0.75	0.60	9.53
EC3	1621	8.49	2 071	1.75	5.94	3.16	5.73	1.23	0.63	8.29
GFRP	1607	2.04	2 000	1.06	4.65	3.58	5.94	0.28	0.53	1.75

图8 典型试样冲击载荷-挠度曲线

Fig.8 Typical sample impact load-deflection curves

表4 试样典型冲击损伤形貌

Table 4 Typical impact damage morphologies of samples

表5 复合材料试样冲击后电热升温特性

Table 5 Electrothermal heating properties of samples after impact

试样组	60s内升温速率/ (℃·s^-1)	最高温度/ ℃	最低温度/ ℃	表面温差/ ℃
EC1	0.777	111.6±2.5	72.4±2.0	39.2±3.5
EC2	0.652	100.7±1.8	78.0±1.7	22.7±1.4
EC3	0.562	97.3±1.3	84.8±1.2	12.5±1.3

图9 典型试样冲击后表面温度-时间曲线

Fig.9 Surface temperature-time curves of typical sample after impact

表6 复合材料试样表面温度分布

Table 6 Surface temperature distribution of samples

图10 典型试样压缩应力-应变曲线

Fig.10 Typical sample compressive stress-strain curves

表7 复合材料试样压缩性能平均值

Table 7 Average value of compression properties of samples

试样组	压缩模量/GPa		压缩强度/MPa
试样组	平均值	变异系数/%	平均值	变异系数/%
EC1	10.87	7.85	131.78	4.62
EC2	11.28	1.12	140.38	3.41
EC3	11.40	1.28	124.35	3.78
GFRP	10.68	1.87	133.49	3.85

表8 典型试样压缩表面应变分布

Table 8 Surface compressive strain distributions of typical samples

图11 试样表面破坏形貌

Fig.11 Surface failure morphologies of samples

图12 典型试样冲击后压缩应力-应变曲线

Fig.12 Compressive stress-strain curves of typical sample after impact

表9 复合材料试样冲击后压缩性能平均值

Table 9 Average values of CAI properties of samples

试样组	冲击后压缩模量/GPa			冲击后压缩强度/MPa
试样组	平均值	变异系数/%	模量保留率/%	平均值	变异系数/%	强度保留率/%
EC1	9.64	5.25	88.73	131.31	1.71	99.64
EC2	10.06	6.54	89.14	139.06	3.08	99.06
EC3	11.08	9.85	97.19	118.09	8.18	94.97
GFRP	9.31	4.79	87.20	132.22	2.03	99.04

表10 典型试样冲击后压缩表面应变分布

Table 10 Surface CAI strain distributions of specimens

图13 冲击后压缩试样表面破坏形貌

Fig.13 Surface failure morphologies of CAI samples

图14 冲击后压缩侧面损伤形貌(放大5倍)

Fig.14 Damage topography of CAI(5×)

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