基于SCARF胶接维修的基础理论和验证研究

发布时间：2018-03-03 10:44

本文选题：碳纤维增强树脂基复合材料(CFRP)　切入点：SCARF胶接维修　出处：《中国民用航空飞行学院》2015年硕士论文　论文类型：学位论文

【摘要】：碳纤维增强树脂基复合材料结构由于其轻质高强、耐疲劳、耐腐蚀等优势性能在航空领域得到了广泛应用,然而,其在整个寿命过程中也不可避免地会遭受各种形式的损伤,如分层、擦伤、裂纹、磨损等。为保证维修后的复合材料结构满足飞机的持续适航性,必须对维修的效果进行相应的验证。本文以波音公司碳纤维/环氧树脂复合材料体系为研究对象,基于SCARF胶接维修方式,主要研究了胶接维修表面微观物理、化学性能与维修效果的内在关联,并采用试验验证方法(MC2)和分析计算验证方法(MC4)验证了维修参数对维修效果的影响,最后针对于实际维修工作提出了维修参数优化的建议。论文的主要研究内容如下： (1)复合材料表/界面微观性能与胶接强度的内在关联研究；基于材料表面/界面微观物理、化学性能,结合机械嵌锁、流变和吸附等胶接理论,从微观本征角度对维修表面性能与胶接强度的内在联系进行了深入研究。 (2)维修参数与复合材料维修效果的影响及其破坏模式研究；基于SCARF胶接维修方式进行了复合材料层压板维修试验,并对试样进行了拉伸力学性能的测试与表征,得到了该修理构型下的四种破坏模式,分析了打磨砂纸目数G、挖补角度β、附加层层数N、RTD(Room temperature and dry condition)/ETW(Elevated temperature and wet condition)环境这四个维修参数对维修效果的影响。 (3)复合材料胶接维修的适航验证研究。采用MC2、MC4方法对维修后的复合材料结构进行适航验证研究。基于复合材料层压板理论,采用ANSYS有限元软件构建了维修附加铺层和挖补角度对维修效果影响的三维模型,计算分析了维修后层压板的极限载荷和失效位置,并将计算结果与力学试验结果进行比对和分析,证明了模型的有效性。基于以上理论研究、试验验证与计算分析,对于采用SCARF维修方式的波音复合材料体系,推荐的维修参数为打磨砂纸目数为100目,挖补角度为4。,附加层数为1层,并建议实际维修工作在常温、通风和湿度较低的环境下进行。
[Abstract]:The structure of resin based composite materials because of its light weight and high strength, fatigue resistance of carbon fiber reinforced, corrosion resistance and other advantages has been widely used in the field of aviation, however, in the whole life process inevitably suffer from various forms of damage, such as delamination, crack, abrasion, wear and so on. In order to ensure the structure of the composite material after repair to meet the airworthiness of the aircraft, must be on the maintenance results in a corresponding verification. In this paper, carbon fiber / epoxy resin composite Boeing system as the research object, SCARF adhesive maintenance mode based on, mainly studies the adhesive surface micro physical maintenance internal connection and maintenance performance, chemical effect, and the experimental verification method (MC2) analysis and verification method (MC4) to verify the effect of maintenance parameters on the maintenance effect, finally in the actual maintenance work put forward maintenance parameter optimization proposal.
The main contents of this paper are as follows:
(1) the internal relationship between the microstructure and the bonding strength of the composite surface / interface;
Based on the material surface / interfacial micro physical, chemical properties, combined with mechanical interlocking, rheological and adsorption bonding theory, in-depth study of internal relations from the perspective of the microscopic intrinsic surface properties of repair and bonding strength.
(2) study on the influence of maintenance parameters and the maintenance effect of composite materials and the failure mode.
SCARF adhesive maintenance mode based on the composite laminate repair test, and the samples were characterized and tested the tensile mechanical properties, the repair of four kinds of failure modes based on, analysis the play matte paper mesh G, scarf angle, additional layer number N, RTD (Room temperature and dry condition /ETW (Elevated) temperature and wet condition) environmental impact of these four parameters on the maintenance maintenance effect.
(3) research on Airworthiness verification of adhesive bonding maintenance for composite materials.
Using MC2, MC4 method of airworthiness for composite structures after repair. The composite laminates based on the theory, constructs a three-dimensional model of maintenance and additional layer patching effect of angle on maintenance effect using ANSYS finite element software, the calculation and analysis of the ultimate load of repaired laminates and failure location, and the calculation results the mechanical test results and comparison and analysis, proved the validity of the model.
Based on the above theory research, analysis of test and calculation for the SCARF maintenance of the Boeing composite system, maintenance parameters recommended for playing matte paper mesh number was 100, at an angle of 4., the additional layer is 1, and that the actual maintenance work at room temperature, through wind and low humidity environment.

【学位授予单位】：中国民用航空飞行学院
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V267

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