Abstract
Surface treatment is typically required to improve the bonding performance of carbon-fiber-reinforced composites. Herein, a wet peel ply was prepared using bismaleimide (BMI) resins as a matrix resin. The temperature–heating rate extrapolation method and rheological method were employed to study the reaction characteristics and viscosity-temperature characteristics of the matrix in the BMI wet peel ply. The curing temperatures of the BMI wet peel ply and the BMI prepreg were the same (200 °C), making this wet peel ply suitable for co-curing with the BMI prepreg. After treatment with the wet peel ply, the bonding strength of the BMI composite joint showed a mean shear strength of 35.5 MPa, which was 1.72% higher than that of the sanded composite and 17.5% higher than that of the composite treated with the dry peel ply. In addition, the BMI composite treated with the BMI wet peel ply exhibited good bonding stability with a coefficient of variation of 3.9. After damp-heat aging for 1440 h, the retention rate of shear strength at room-temperature was 82.3%. The relatively loosely woven carrier in the BMI wet peel ply increased the surface roughness of the composite, thus improving the bonding strength.
Highlights
Carbon-fiber-reinforced polymer (CFRP) composites, which have better specific strength [1], specific [2], corrosion resistance [3], and fatigue resistance [4] than other materials, are increasingly used in the aviation industry [5,6,7]
The viscosity of the matrix resin decreased continuously as the temperature increased up to 50 ◦C, whereas the viscosity changed insignificantly with temperature when the temperature was above 60 ◦C, indicating that that the viscosity of the resin before curing is temperature-dependent and that the temperature is a critical parameter in the manufacturing process of wet peel plies
The composite treated with the J-412 BMI wet peel ply showed a mean shear strength of 35.5 MPa, which was 1.72% than that of the sanded composite and 17.5% higher than that of the composite treated with the dry peel ply
Summary
Carbon-fiber-reinforced polymer (CFRP) composites, which have better specific strength [1], specific [2], corrosion resistance [3], and fatigue resistance [4] than other materials, are increasingly used in the aviation industry [5,6,7]. The connection technology of CFRPs mainly includes bonding connection [8] and mechanical connection [9,10]. The mechanical connection can transmit large loads, but the holes on the CFRPs will cause serious stress concentration [11], which will weaken the strength of the material. The bonding has the advantages of excellent fatigue resistance, high connection efficiency, and large load transfer. It has become the main connection technology for CFRP materials in the aerospace field [12]. The bonding of CFRPs includes co-curing, co-bonding, and secondary bonding [13]. The CFRP laminate is used in co-bonding and secondary bonding [14,15,16,17], so the surface treatment has an important influence on the bonding performance [18,19]
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