本文選題：碳纖維增強(qiáng)樹脂基復(fù)合材料(CFRP)　切入點(diǎn)：SCARF膠接維修　出處：《中國(guó)民用航空飛行學(xué)院》2015年碩士論文　論文類型：學(xué)位論文

【摘要】：碳纖維增強(qiáng)樹脂基復(fù)合材料結(jié)構(gòu)由于其輕質(zhì)高強(qiáng)、耐疲勞、耐腐蝕等優(yōu)勢(shì)性能在航空領(lǐng)域得到了廣泛應(yīng)用,然而,其在整個(gè)壽命過程中也不可避免地會(huì)遭受各種形式的損傷,如分層、擦傷、裂紋、磨損等。為保證維修后的復(fù)合材料結(jié)構(gòu)滿足飛機(jī)的持續(xù)適航性,必須對(duì)維修的效果進(jìn)行相應(yīng)的驗(yàn)證。本文以波音公司碳纖維/環(huán)氧樹脂復(fù)合材料體系為研究對(duì)象,基于SCARF膠接維修方式,主要研究了膠接維修表面微觀物理、化學(xué)性能與維修效果的內(nèi)在關(guān)聯(lián),并采用試驗(yàn)驗(yàn)證方法(MC2)和分析計(jì)算驗(yàn)證方法(MC4)驗(yàn)證了維修參數(shù)對(duì)維修效果的影響,最后針對(duì)于實(shí)際維修工作提出了維修參數(shù)優(yōu)化的建議。 論文的主要研究?jī)?nèi)容如下： (1)復(fù)合材料表/界面微觀性能與膠接強(qiáng)度的內(nèi)在關(guān)聯(lián)研究； 基于材料表面/界面微觀物理、化學(xué)性能,結(jié)合機(jī)械嵌鎖、流變和吸附等膠接理論,從微觀本征角度對(duì)維修表面性能與膠接強(qiáng)度的內(nèi)在聯(lián)系進(jìn)行了深入研究。 (2)維修參數(shù)與復(fù)合材料維修效果的影響及其破壞模式研究； 基于SCARF膠接維修方式進(jìn)行了復(fù)合材料層壓板維修試驗(yàn),并對(duì)試樣進(jìn)行了拉伸力學(xué)性能的測(cè)試與表征,得到了該修理構(gòu)型下的四種破壞模式,分析了打磨砂紙目數(shù)G、挖補(bǔ)角度β、附加層層數(shù)N、RTD(Room temperature and dry condition)/ETW(Elevated temperature and wet condition)環(huán)境這四個(gè)維修參數(shù)對(duì)維修效果的影響。 (3)復(fù)合材料膠接維修的適航驗(yàn)證研究。 采用MC2、MC4方法對(duì)維修后的復(fù)合材料結(jié)構(gòu)進(jìn)行適航驗(yàn)證研究�；趶�(fù)合材料層壓板理論,采用ANSYS有限元軟件構(gòu)建了維修附加鋪層和挖補(bǔ)角度對(duì)維修效果影響的三維模型,計(jì)算分析了維修后層壓板的極限載荷和失效位置,并將計(jì)算結(jié)果與力學(xué)試驗(yàn)結(jié)果進(jìn)行比對(duì)和分析,證明了模型的有效性。 基于以上理論研究、試驗(yàn)驗(yàn)證與計(jì)算分析,對(duì)于采用SCARF維修方式的波音復(fù)合材料體系,推薦的維修參數(shù)為打磨砂紙目數(shù)為100目,挖補(bǔ)角度為4。,附加層數(shù)為1層,并建議實(shí)際維修工作在常溫、通風(fēng)和濕度較低的環(huán)境下進(jìn)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.

【學(xué)位授予單位】：中國(guó)民用航空飛行學(xué)院
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：V267

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