基于RTM技术的碳纤维/聚酰亚胺复合材料舵面一体化制备与验证

江晟达; 罗楚养; 张朋; 文子豪; 蔡培培

doi:10.13801/j.cnki.fhclxb.20200429.002

基于RTM技术的碳纤维/聚酰亚胺复合材料舵面一体化制备与验证

doi: 10.13801/j.cnki.fhclxb.20200429.002

江晟达^1,,
罗楚养^{1, 2, ,},
张朋^3,,
文子豪^1,,
蔡培培^2,

1.
东华大学　民用航空复合材料协同创新中心，上海 201620
2.
中国空空导弹研究院，洛阳 471009
3.
航空工业复合材料技术中心　先进复合材料重点实验室，北京 101300

基金项目: 航空科学基金(20180112008)；青年人才托举工程(2016QNRC001)；东华大学青年教师科研启动基金

详细信息

通讯作者:
罗楚养，博士，高级工程师，研究方向为复合材料结构设计与分析　E-mail：cyluo@dhu.edu.cn

中图分类号: TB332；V214.8
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出版历程
- 收稿日期: 2020-03-16
- 录用日期: 2020-04-25
- 网络出版日期: 2020-04-30
- 刊出日期: 2020-09-15

Integration manufacturing and testing verification for RTMable carbon fiber/polyimide composite rudder

JIANG Shengda^1
,,
LUO Chuyang^{1, 2
, ,},
ZHANG Peng^3
,,
WEN Zihao^1
,,
CAI Peipei^2
,

1.
Collaborative Innovation Center for Civil Aviation Composites, Donghua University, Shanghai 201620, China
2.
China Airborne Missile Academy, Luoyang 471009, China
3.
Science and Technology on Advanced Composites Laboratory, AVIC Composite Technology Center, Beijing 101300, China

摘要

摘要: 设计了一种碳纤维/聚酰亚胺复合材料舵面结构，采用PAM-RTM软件模拟了舵面在注胶过程中的树脂流动，根据模拟结果设计了成型模具，并通过树脂传递模塑(RTM)工艺制备了耐高温碳纤维/聚酰亚胺复合材料舵面，对其进行了力学试验，并将三维有限元分析结果与试验结果对比。试验结果表明，碳纤维/聚酰亚胺复合材料舵面在150%的使用载荷下保持了结构的完整性，骨架的最大应变为2 408×10^–6，复合材料蒙皮的最大应变为2 371×10^–6。有限元分析结果表明，金属骨架的最大应力出现在舵轴根部圆弧过渡区，而碳纤维/聚酰亚胺复合材料蒙皮的最大应力出现在与垫片外圆弧接触处；碳纤维/聚酰亚胺复合材料舵面的初始破坏为蒙皮单向带横向拉伸失效。
- 复合材料 /
- 舵面 /
- 聚酰亚胺 /
- 树脂传递模塑 /
- 破坏机制
Abstract: The carbon fiber/polyimide composite rudder was designed. And the PAM-RTM software was used to simulate the resin flow of the rudder during the injection process. The forming die was designed according to the simulation results. The high-temperature resistant carbon fiber/polyimide composite rudder was fabricated via resin transfer molding (RTM) process accordingly and the mechanical properties under bending load were investigated to compare with the 3D finite element analysis (FEA) results. The experimental results show that the carbon fiber/polyimide composite rudder maintains the structural integrity under 150% of the service load. The maximum strain of the metal skeleton is 2 408×10^–6, and the maximum strain of the carbon fiber/polyimide composite skin is 2 371×10^–6. The FEA results reveal that the maximum stress of the metal skeleton appears at the arc transitional region of the rudder shaft root, while the maximum stress of the carbon fiber/polyimide composite skin emerges in the resin junctional area of the gasket outer arc. The initial damage of the carbon fiber/polyimide composite rudder is the transverse tensile failure of the skin unidirectional tape.
- composite /
- rudder /
- polyimide /
- resin transfer molding /
- failure mechanism

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图 1 碳纤维/聚酰亚胺复合材料舵面结构

Figure 1. Structure of carbon fiber/polyimide composite rudder

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图 2 碳纤维/聚酰亚胺复合材料舵面前缘注射时树脂流动情况

Figure 2. Resin flow of carbon fiber/polyimide composite rudder by leading edge injection

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图 3 碳纤维/聚酰亚胺复合材料舵面后缘注射时树脂流动情况

Figure 3. Resin flow of carbon fiber/polyimide composite rudder by trailing edge injection

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图 4 碳纤维/聚酰亚胺复合材料舵面注胶模具

Figure 4. Injection mold of carbon fiber/polyimide composite rudder

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图 5 铺覆完成的碳纤维/聚酰亚胺复合材料舵面

Figure 5. Carbon fiber/polyimide composite rudder after draping

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图 6 碳纤维/聚酰亚胺复合材料舵面成品

Figure 6. Carbon fiber/polyimide composite rudder product

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图 7 碳纤维/聚酰亚胺复合材料舵面静强度试验

Figure 7. Static strength test of carbon fiber/polyimide composite rudder

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图 8 碳纤维/聚酰亚胺复合材料舵面的载荷-位移曲线

Figure 8. Load-displacement curve of carbon fiber/polyimide composite rudder

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图 9 金属骨架载荷-应变曲线

Figure 9. Load-strain curves of metal framework

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图 10 碳纤维/聚酰亚胺复合材料蒙皮载荷-应变曲线

Figure 10. Load-strain curves of carbon fiber/polyimide composite skin

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图 11 碳纤维/聚酰亚胺复合材料舵面有限元模型

Figure 11. Finite element model of carbon fiber/polyimide composite rudder

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图 12 碳纤维/聚酰亚胺复合材料舵面载荷-位移曲线

Figure 12. Load-displacement curves of carbon fiber/polyimide composite rudder

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图 13 碳纤维/聚酰亚胺复合材料蒙皮纵向应变-载荷曲线

Figure 13. Longitudinal strain-load curves of carbon fiber/polyimide composite skin

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图 14 金属骨架应力-载荷曲线

Figure 14. Stress-load curves of metal framework

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图 15 碳纤维/聚酰亚胺复合材料舵面位移分布

Figure 15. Displacement distribution of carbon fiber/polyimide composite rudder

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图 16 金属骨架和树脂连接区等效应力分布

Figure 16. Equivalent stress distribution of metal framework and resin junctional area

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图 17 胶层及金属垫片应力分布

Figure 17. Stress distribution of adhesive layer and metal gasket

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图 18 铆钉及金属前缘应力分布

Figure 18. Stress distribution of rivets and metal leading edge

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图 19 碳纤维/聚酰亚胺复合材料蒙皮应力分布

Figure 19. Stress distribution of carbon fiber/polyimide composite skin

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表 1 U3160单向无纬帘子布碳纤维布和CF3031斜纹碳纤维机织物材料性能

Table 1. Material properties of U3160 no-weft carbon-fiber cord fabric and CF3031 twill carbon-fiber woven fabric

Project	Direction	CF3031	U3160
Ply thickness/mm		0.30±0.02	0.167
Areal density/(g·m⁻²)		220±7	160±10
Fabric density/ (tow·(100 mm)⁻¹)	warp-wise	54±2	80±4
Fabric density/ (tow·(100 mm)⁻¹)	weft-wise	54±2	40±2
Tensile breaking strength/ (N·25 mm)	warp-wise	≥1 600	1 800
Tensile breaking strength/ (N·25 mm)	weft-wise	≥1 600	—

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表 2 RTM350聚酰亚胺树脂基本性能

Table 2. Basic properties of RTM350 polyimide

Molecule weight/(g·mol^–1)	Minimum viscosity/ (Pa·s)	270℃ viscosity/(Pa·s)	Process period/h
1 066	0.39	0.61	3–4
T_g (E′) /℃	T_g (tanδ) /℃	5% decomposition temperature/℃
361	392	537
Notes: T_g(E′)—Glass transition temperatures; T_g(tanδ)—Glass transition temperatures based on onset decline of storage modulus.

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表 3 材料力学性能参数

Table 3. Mechanical properties of materials

	U3160/RTM350		CF3031/RTM350
X_t/Y_t/MPa	1 397/47.9		612.9/470.8
E_1t/E_2t/GPa	117/9.65		68/52
υ₁₂	0.3		0.035
υ₁₃/υ₂₃	0.15		0.15
X_c/Y_c/MPa	1 004/223		608/507.5
G₁₂/GPa	4.69		4.4
τ₁₂/MPa	86		86
G₁₃/G₂₃/GPa	3.5		3.5
τ₁₃/τ₂₃/MPa	93		93
Ply thickness/mm	0.167		0.2
	RTM350	TC4	Stainless steel
X_t/Y_t /MPa	47.9	900	850
E_1t/E_2t /GPa	3.5	110	200
υ₁₂	0.3	0.3	0.3
Notes: E_1t, E_2t—Tensile elastic moduli; υ₁₂, υ₁₃, υ₂₃—Poisson’s ratios; G₁₂, G₁₃, G₂₃—Shear moduli; X_t—Longitudinal tensile strength; X_c—Longitudinal compressive strength; Y_t—Transverse tensile strength; Y_c—Transverse compressive strength; τ₁₂—In-plane shear stress; τ₁₃, τ₂₃—Interlaminar shear stresses.

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