【摘要】：碳纖維增強(qiáng)復(fù)合材料(CFRP)具有比重小、比強(qiáng)度高、比模量高、耐高溫、抗疲勞及耐化學(xué)腐蝕性能好等優(yōu)點(diǎn)而被廣泛應(yīng)用于航天器主次受力構(gòu)件及部分功能件。航天器用復(fù)合材料在服役期間會(huì)受到溫度、濕度及紫外線輻射等各種嚴(yán)苛環(huán)境因素的影響,其中濕熱環(huán)境是導(dǎo)致復(fù)合材料性能發(fā)生退化的最為重要的因素之一。目前,碳纖維增強(qiáng)復(fù)合材料濕熱性能的研究主要集中在單一的濕、熱或濕熱條件,而彎曲載荷加載和濕熱循環(huán)環(huán)境作用對(duì)碳纖維增強(qiáng)復(fù)合材料性能的研究尚少,因此研究碳纖維增強(qiáng)復(fù)合材料在濕熱老化環(huán)境下外加彎曲載荷對(duì)其力學(xué)性能的影響規(guī)律具有重要意義。本文為探究不同孔隙率碳纖維/環(huán)氧樹脂層合板在高低溫濕熱老化環(huán)境及外加載荷作用下力學(xué)性能的演變,基于材料服役期間的吸濕狀態(tài)和內(nèi)應(yīng)力狀態(tài),對(duì)T700CF/3234EP進(jìn)行高低溫交變加速濕熱循環(huán)老化試驗(yàn)。通過(guò)控制模壓壓力,制備3種孔隙率分別為0.04、0.08和0.11的層合板,將3種孔隙率的層合板進(jìn)行加載,加載載荷分別為層合板最大彎曲載荷的0、30%、40%和60%,然后將其置于高低溫環(huán)境模擬試驗(yàn)箱中,分別研究不同循環(huán)周期復(fù)合材料層合板的結(jié)構(gòu)與力學(xué)性能變化,并采用ABAQUS軟件對(duì)其力學(xué)性能進(jìn)行有限元模擬,最后預(yù)測(cè)了層合板在濕熱循環(huán)、彎曲載荷單獨(dú)與耦合作用下的使用壽命。試驗(yàn)結(jié)果表明:層合板的孔隙多分布于富樹脂區(qū)和層與層之間的界面區(qū)域附近。相同的孔隙率層合板,隨著濕熱循環(huán)周期的增加,孔隙數(shù)量增加明顯,同一孔隙的變化并不明顯,非常接近的孔隙,孔隙之間會(huì)連通起來(lái)形成更大的孔隙。加載后的層合板恰好相反,隨著外加載荷的增大,單個(gè)的孔隙明顯增大,孔隙的數(shù)量增加并不明顯。隨著高低溫濕熱循環(huán)周期的增加,彎曲和拉伸強(qiáng)度均呈現(xiàn)下降趨勢(shì)�？紫堵试酱蟮膶雍习�,彎曲和拉伸強(qiáng)度下降越大。濕熱循環(huán)的破壞機(jī)制主要是使纖維與樹脂的脫粘。相同沖擊能量下,濕熱老化后層合板的凹坑深度小于沒(méi)有經(jīng)過(guò)濕熱老化的層合板。隨著沖擊能量的增大,凹坑深度增加,從7.5J增加到10J時(shí),層合板的凹坑深度會(huì)出現(xiàn)突變。隨著濕熱周期的增加,孔隙率越大的層合板剩余壓縮強(qiáng)度下降越大。加載40%和60%的層合板在4-6周期時(shí),分別增加了1.5%和1.6%。加載越大的層合板固化度提高越大,進(jìn)而巴氏硬度提高越大,玻璃化轉(zhuǎn)變溫度下降越明顯,但層合板的化學(xué)結(jié)構(gòu)基本沒(méi)變。隨著濕熱老化周期的增加,孔隙率和彎曲載荷越大,彎曲和拉伸強(qiáng)度下降越大,層合板分層和纖維脫粘現(xiàn)象越明顯,在4-6周期時(shí),由于樹脂的二次固化,加載40%和60%載荷的層合板的彎曲和拉伸強(qiáng)度變化趨于平緩。隨著濕熱周期的增加,孔隙率相同的層合板,彎曲載荷越大,相同的沖擊能量沖擊后,凹坑深度越小;而外加彎曲載荷一樣時(shí),孔隙率越大,相同的沖擊能量沖擊后,凹坑深度越大。用ABAQUS軟件模擬得到的彎曲、拉伸及沖擊力學(xué)性能的模擬值與試驗(yàn)值非常吻合,并通過(guò)對(duì)層合板每一層的彎曲、拉伸和沖擊力學(xué)性能的模擬,發(fā)現(xiàn)層合板每一層的彎曲、拉伸和沖擊力學(xué)性能變化規(guī)律都是對(duì)稱分布的,并且中間兩層的強(qiáng)度最小。壽命預(yù)測(cè)結(jié)果顯示濕熱環(huán)境和外加彎曲載荷都大大減少了層合板的使用壽命
[Abstract]:The carbon fiber reinforced composite (CFRP) has the advantages of small specific gravity, high specific strength, high specific modulus, high temperature resistance, fatigue resistance and chemical corrosion resistance. The composite material for spacecraft is affected by various severe environmental factors such as temperature, humidity and ultraviolet radiation during service, and the damp-heat environment is one of the most important factors leading to the degradation of the performance of the composite material. At present, the research on the heat and heat performance of the carbon fiber reinforced composite material is mainly concentrated on a single wet, hot or wet heat condition, and the research on the performance of the carbon fiber reinforced composite material is low due to the action of the bending load loading and the damp-heat circulation environment. Therefore, it is of great significance to study the influence of the applied bending load on the mechanical properties of the carbon fiber reinforced composite in the damp-heat aging environment. In order to investigate the evolution of mechanical properties of different porosity carbon fiber/ epoxy resin laminated plates under the influence of high and low temperature damp-heat aging environment and the applied load, the high and low temperature and high-temperature alternating-accelerated wet-heat cycle aging test was carried out on the T700CF/ 3234EP based on the moisture absorption state and the internal stress state during the service period of the material. by controlling the compression pressure, three kinds of laminated plates with the porosity of 0.04, 0.08 and 0.11 are prepared, the three kinds of porosity laminated plates are loaded, the loading load is 0,30%,40% and 60% of the maximum bending load of the laminated plates, and then the laminated plates are placed in a high and low temperature environment simulation test box, The structural and mechanical properties of the composite laminates with different cycle cycles were studied. The mechanical properties of the composite laminates were simulated by using the ABAQUS software, and the service life of the laminated plates under the heat and heat cycle and the bending load was predicted. The results show that the porosity of the laminated plate is distributed in the vicinity of the interface area between the rich resin area and the layer and the layer. In the same porosity laminated plate, with the increase of the heat-heat circulation period, the number of pores is increased, and the variation of the same pore is not obvious, and the pores are very close, and the pores are communicated with each other to form larger pores. The loaded laminated plate is just opposite, with the increase of the applied load, the single pore is obviously enlarged, and the number of the pores is not obvious. With the increase of the high and low temperature and hot-heat cycle, both the bending and the tensile strength show a downward trend. The larger the porosity, the greater the bending and tensile strength. The mechanism of the heat-and-heat circulation is the debonding of the fiber and the resin. Under the same impact energy, the depth of the pit of the laminated plate after the damp-heat aging is less than that of the laminated plate which is not subjected to heat and heat aging. As the impact energy increases, the depth of the pit increases, from 7.5J to 10J, the depth of the pit of the laminated plate will change. With the increase of the damp-heat period, the larger the residual compressive strength of the laminated plate with the larger the porosity. The loading of 40% and 60% of the laminate increased by 1.5% and 1.6% at 4-6 cycles, respectively. The higher the curing degree of the laminated plate with the larger the loading, the greater the hardness of the glass transition, the more obvious the glass transition temperature, but the chemical structure of the laminated plate is basically unchanged. With the increasing of damp-heat aging period, the greater the porosity and bending load, the greater the bending and tensile strength, the more obvious the delamination of the laminated plates and the debonding of the fibers, and, at the time of 4-6, due to the secondary curing of the resin, The bending and tensile strength of the laminated plates loaded with 40% and 60% of the load tended to be gentle. With the increase of the damp-heat period, the larger the porosity, the larger the bending load, the smaller the depth of the pit after the same impact energy, and the larger the porosity, the greater the depth of the pit after the same impact energy. The simulated values of the bending, tensile and impact mechanical properties obtained by the ABAQUS software are in good agreement with the experimental values, and the bending, tensile and impact mechanical properties of each layer of the laminated plate are simulated, and the bending of each layer of the laminated plate is found. The variation of tensile and impact mechanical properties is distributed symmetrically, and the strength of the middle two layers is the least. The life prediction results show that the damp-heat environment and the applied bending load greatly reduce the service life of the laminated plate.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：TB332

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