钛板表面处理工艺对钛板与复合材料粘接性能影响
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摘要
纤维增强钛合金层板(TiGr)是纤维金属层板中综合性能最优异的层板之一,被广泛应用于航空结构中。TiGr层板中钛板与复合材料的粘接性能会影响TiGr层板的刚度和失效模式,而钛板与复合材料的粘接性能受工艺影响较大。采用浮辊剥离试验和极差分析方法,研究了钛板表面处理工艺对钛板与复合材料粘接性能的影响。试验表明进行两次等离子体处理工艺的钛板与复合材料粘接件的剥离强度最高,为6. 914 kN/m,而进行两次等离子体处理和树脂防护的钛板与复合材料粘接件的剥离强度最低,为2. 139 kN/m。在剥离过程中,钛板与复合材料粘接界面存在三种破坏模式:钛板与胶膜的粘附破坏、胶膜的内聚破坏、胶膜与复合材料的粘附破坏,发生胶膜的内聚破坏时,钛板与复合材料的粘接性能最好。钛板表面进行树脂防护,钛板与复合材料的粘接性能降低。钛板表面进行等离子体处理之前进行喷砂处理,获得的钛板与复合材料的粘接性能弱于仅进行等离子体处理获得的钛板与复合材料的粘接性能。
The Titanium/Graphite Hybrid Laminates( TiGr) have been widely used in aeronautical structures for their excellent performance. The adhesive properties of the titanium plate and the composite in the TiGr laminates will affect the stiffness and failure modes of the TiGr laminates. However,the adhesive property of the titanium plate and the composite are greatly influenced by the processing technology. In this paper,adhesive property of titaniumcomposite joints with different surface treatments on titanium surface was investigated based on floating roll peeling methods and range analysis. The peeling results show that the titanium-composite joints with twice plasma treatment have the highest peeling resistance of 6. 914 kN/m,but the titanium-composite joints with twice plasma treatment and resin protection have the the lowest peeling resistance,which is 2. 139 kN/m. Three failure patterns of the adhesive interface between titanium and composite happen during the peeling process. That is the adhesion failure between the titanium plate and the adhesive film,the cohesion failure of the adhesive film,and the adhesion failure between the adhesive film and the composite. The peel resistance reaches the highest when the cohesion failure of the adhesive film occurs. According to the experimental results,the adhesive property is weakened with the resin protection applied on the titanium surface. In addition,the grit blasting prior to the plasma treatment weakens the adhesive property,as compared to the property with no grit blasting prior to plasma treatment.
The Titanium/Graphite Hybrid Laminates( TiGr) have been widely used in aeronautical structures for their excellent performance. The adhesive properties of the titanium plate and the composite in the TiGr laminates will affect the stiffness and failure modes of the TiGr laminates. However,the adhesive property of the titanium plate and the composite are greatly influenced by the processing technology. In this paper,adhesive property of titaniumcomposite joints with different surface treatments on titanium surface was investigated based on floating roll peeling methods and range analysis. The peeling results show that the titanium-composite joints with twice plasma treatment have the highest peeling resistance of 6. 914 kN/m,but the titanium-composite joints with twice plasma treatment and resin protection have the the lowest peeling resistance,which is 2. 139 kN/m. Three failure patterns of the adhesive interface between titanium and composite happen during the peeling process. That is the adhesion failure between the titanium plate and the adhesive film,the cohesion failure of the adhesive film,and the adhesion failure between the adhesive film and the composite. The peel resistance reaches the highest when the cohesion failure of the adhesive film occurs. According to the experimental results,the adhesive property is weakened with the resin protection applied on the titanium surface. In addition,the grit blasting prior to the plasma treatment weakens the adhesive property,as compared to the property with no grit blasting prior to plasma treatment.
引文
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[20] Standards I. Adhesives-designation of main failure patterns[S]. 1992.
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[3]徐凤娟. Ti/APC-2复合层板基本力学性能的有限元模拟研究[D].南京:南京航空航天大学,2013.
[4]郑兴伟,何雪婷,刘红兵,等.纤维铝合金层板的研究进展[J].材料导报,2013,27(s1):347-350.
[5]吴志恩.纤维金属层板在飞机制造中的应用及工艺性分析[J].航空制造技术,2013,421(Z1):137-139.
[6]贾新强,郎利辉.纤维金属层板制备成形的研究现状及发展趋势[J].精密成形工程,2017,9(2):1-6.
[7]王永贵,梁宪珠.纤维金属层板技术与大型飞机[C]//玻璃钢/复合材料学术年会. 2010.
[8] Yamaguchi T,Okabe T,Yashiro S. Fatigue simulation for titanium/CFRP hybrid laminates using cohesive elements[J]. Composites Science&Technology,2009,69(11-12):1968-1973.
[9] Asghar W,Nasir M A,Qayyum F,et al. Investigation of fatigue crack growth rate in CARALL,ARALL and GLARE[J]. Fatigue&Fracture of Engineering Materials&Structures, 2017, 40(7):1086-1100.
[10]Zhang P F,Churi N J,Pei Z J,et al. Mechanical drilling processes for titanium alloys:A literature review[J]. Machining Science&Technology,2008,12(4):417-444.
[11]徐飞.优化Ti/PEEK粘结性能的钛板表面处理工艺研究[D].南京:南京航空航天大学,2014.
[12] Su Y,Rooij M D,Grouve W,et al. The effect of titanium surface treatment on the interfacial strength of titanium-thermoplastic composite joints[J]. International Journal of Adhesion&Adhesives,2016,72:98-108.
[13] Leahy W,Barron V,Buggy M,et al. Plasma surface treatment of aerospace materials for enhanced adhesive bonding[J]. Journal of Adhesion,2001,77(3):215-249.
[14]Molitor P,Barron V,Young T. Surface treatment of titanium for adhesive bonding to polymer composites:a review[J]. International Journal of Adhesion&Adhesives,2001,21(2):129-136.
[15] Li X,Zhang X,Zhang H,et al. Mechanical behaviors of Ti/CFRP/Ti laminates with different surface treatments of titanium sheets[J]. Composite Structures,2017,163:21-31.
[16] Cobb T Q,Johnson W S,Lowther S E,et al. Optimization of surface treatment and adhesive selection for bond durability in Ti-15-3laminates[J]. Journal of Adhesion,1999,71(2-3):115-141.
[17] Truong H T,Lagoudas D C,Ochoa O O,et al. Fracture toughness of fiber metal laminates:Carbon nanotube modified Ti-polymer-matrix composite interface[J]. Journal of Composite Materials,2014,48(22):2697-2710.
[18]张文刚.高强度胶粘剂剥离强度的测定浮辊法:GB/T 7122—1996[S].上海:上海胶制品研究所,1996.
[19]李红宇,李志华,郑雪岩,等.胶粘剂剥离强度试验数据处理分析[J].哈尔滨理工大学学报,1999(1):60-62.
[20] Standards I. Adhesives-designation of main failure patterns[S]. 1992.