本文關(guān)鍵詞：溫度環(huán)境下復(fù)合材料層合結(jié)構(gòu)疲勞壽命預(yù)測方法研究　出處：《南京航空航天大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

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【摘要】：復(fù)合材料層合結(jié)構(gòu)作為航空航天結(jié)構(gòu)的關(guān)鍵材料近年來廣泛使用于各種航空航天結(jié)構(gòu)中,并收到了良好的減重、抗疲勞、曲面外形優(yōu)異等效果。隨著復(fù)合材料的深入應(yīng)用,對其在溫度環(huán)境下的疲勞行為的研究顯得必要而緊迫。首先,本文提出并建立了基于最弱環(huán)理論的層合結(jié)構(gòu)靜強(qiáng)度/疲勞壽命預(yù)測方法。從單層板強(qiáng)度與疲勞壽命服從Weibull分布出發(fā),基于概率理論及最弱環(huán)理論,以層合板的每一單層作為研究對象,認(rèn)為層合板是由各單層串聯(lián)的環(huán),一旦某一層發(fā)生了失效,整個(gè)層合結(jié)構(gòu)便發(fā)生失效。基于該學(xué)術(shù)觀點(diǎn),推導(dǎo)建立了層合板失效概率與單層板失效概率之間的關(guān)系,即層合板失效概率與單層板特征壽命、疲勞循環(huán)以及分散系數(shù)之間的關(guān)系,結(jié)合單層板的等壽命曲線,建立了復(fù)合材料層合板的強(qiáng)度/疲勞壽命預(yù)測方法。引用文獻(xiàn)中的T300/BMP316層合板在室溫下的靜強(qiáng)度/疲勞壽命試驗(yàn)數(shù)據(jù),采用該方法對層合板的拉伸強(qiáng)度與疲勞壽命進(jìn)行預(yù)測,靜強(qiáng)度預(yù)測誤差在8%以內(nèi),疲勞壽命預(yù)測誤差在三倍誤差帶之內(nèi)。其次,將最弱環(huán)理論與有限元方法相結(jié)合,提出并建立了基于最弱環(huán)理論的層合結(jié)構(gòu)靜強(qiáng)度/疲勞壽命有限元預(yù)測方法。認(rèn)為單元內(nèi)任意一點(diǎn)發(fā)生失效,則整個(gè)單元便發(fā)生失效;當(dāng)失效單元擴(kuò)展到整個(gè)結(jié)構(gòu)無法承載時(shí),則整個(gè)結(jié)構(gòu)便發(fā)生失效�；诖�,推導(dǎo)了單元失效概率與單層板失效概率之間的關(guān)系即單元失效概率與單層板特征壽命、疲勞循環(huán)以及分散系數(shù)之間的關(guān)系,建立了相應(yīng)的有限元預(yù)測方法。引用文獻(xiàn)中的層合板接頭的疲勞試驗(yàn)數(shù)據(jù),采用該方法對層合板接頭的疲勞壽命預(yù)測誤差在三倍誤差帶之內(nèi)。然后,本文采用Mivehchi的溫度與單層板剛度/強(qiáng)度公式,得到溫度環(huán)境下單層板的強(qiáng)度/剛度與溫度的關(guān)系式,并用于修正室溫下的單層板等壽命曲線,即特征疲勞壽命與溫度環(huán)境下應(yīng)力的關(guān)系式,從而解決了溫度環(huán)境下的復(fù)合材料層合板結(jié)構(gòu)的強(qiáng)度與壽命設(shè)計(jì)分析難題。同時(shí),為了驗(yàn)證本文提出的預(yù)測方法在溫度環(huán)境下的有效性,本文進(jìn)行了溫度環(huán)境下的層合板靜強(qiáng)度和疲勞壽命預(yù)測計(jì)算與試驗(yàn)驗(yàn)證。開展了基于T300/BMP316層合板溫度環(huán)境下靜強(qiáng)度/疲勞試驗(yàn)研究,得到了T300/BMP316層合板的靜強(qiáng)度/疲勞壽命數(shù)據(jù)。采用本文提出的方法編制了ANSYS APDL程序?qū)ζ潇o強(qiáng)度/疲勞壽命進(jìn)行預(yù)測并與試驗(yàn)結(jié)果比較,靜強(qiáng)度預(yù)測值誤差都在±10%以內(nèi),100?C下的疲勞壽命預(yù)測值在1倍誤差帶之內(nèi),200?C下的疲勞壽命預(yù)測值在2倍誤差帶之內(nèi)。且單元失效形式與斷件吻合,證明了該方法的有效性。
[Abstract]:Composite laminated structure, as the key material of aerospace structure, has been widely used in various aerospace structures in recent years, and has received good weight loss and fatigue resistance. With the further application of composite materials, it is necessary and urgent to study its fatigue behavior in temperature environment. First of all. A prediction method for static strength / fatigue life of laminated structures based on the weakest ring theory is proposed and established in this paper. Based on the Weibull distribution of the strength and fatigue life of single layer plates. Based on the probability theory and the weakest ring theory, every single layer of laminated plate is considered as the ring in series by each layer. Based on this academic viewpoint, the relationship between the failure probability of laminated plate and the failure probability of single-layer plate is derived, that is, the failure probability of laminated plate and the characteristic life of single-layer plate. The relationship between fatigue cycle and dispersion coefficient is combined with the equal-life curve of single-layer plate. A method for predicting the strength / fatigue life of composite laminates was established, and the static strength / fatigue life test data of T300 / BMP316 laminates at room temperature were cited. The method is used to predict the tensile strength and fatigue life of laminated plates. The prediction error of static strength is less than 8%, and the prediction error of fatigue life is within three times error band. By combining the weakest ring theory with the finite element method, a finite element method for predicting the static strength / fatigue life of laminated structures based on the weakest ring theory is proposed and established. Then the whole unit becomes invalid; When the failure element is extended to the entire structure, the whole structure will fail. Based on this. The relationship between the failure probability of the element and the failure probability of the single-layer plate is deduced, that is, the relationship between the failure probability of the element and the characteristic life, fatigue cycle and dispersion coefficient of the single-layer plate. The corresponding finite element prediction method is established, and the fatigue life prediction error of laminated joints is within three times of the error band by using the fatigue test data of laminated joints in the literature. In this paper, the formula of the relationship between the strength / stiffness and the temperature of the single-layer plate is obtained by using the formula of Mivehchi's temperature and the stiffness / strength of the monolayer plate, and the equation is used to modify the isobarth curve of the single-layer plate at room temperature. The relationship between the characteristic fatigue life and the stress in temperature environment can solve the problem of strength and life design of composite laminated plate structure under temperature environment. At the same time. In order to verify the effectiveness of the proposed prediction method in the temperature environment. In this paper, the static strength and fatigue life of laminated plates under temperature environment are calculated and verified. The static strength / fatigue test of laminated plates based on T300 / BMP316 is carried out. The static strength / fatigue life data of T300 / BMP316 laminates are obtained. The ANSYS is compiled by the method proposed in this paper. The static strength / fatigue life of the program was predicted by APDL and compared with the test results. The error of static strength prediction is within 鹵10%? The prediction value of fatigue life under C is 200? The prediction value of fatigue life under C is within the error band of 2 times, and the failure form of the element is in agreement with that of the broken part, which proves the validity of the method.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2015
【分類號】：TB332

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