【摘要】：碳纖維復(fù)合材料逐漸成為了航空航天領(lǐng)域中重要的材料之一,從一開始用于飛機(jī)中的次要部件,到現(xiàn)在大量使用與主承力結(jié)構(gòu)中,復(fù)合材料體現(xiàn)著它在工業(yè)上的重要地位。但飛機(jī)的結(jié)構(gòu)復(fù)雜,并且由于布線和維修等原因,其承載部件不得不面臨開孔的問題,而應(yīng)力集中現(xiàn)象的存在,開孔會對承載部件的力學(xué)性能造成極大的削弱。同時(shí),復(fù)合材料力學(xué)性能具有顯著的分散性,因此我們除了需要對含開孔部件進(jìn)行正確的剩余強(qiáng)度評估以外,還需要對其進(jìn)行合理的安全性與可靠性的評估。因而,對使用復(fù)合材料制備的承載構(gòu)件做出合理的可靠性、剩余強(qiáng)度、損傷容限設(shè)計(jì)與分析是航空航天器械中承載部件力學(xué)性能評價(jià)中尤為重要的環(huán)節(jié)。剩余強(qiáng)度評價(jià)是含開孔復(fù)合材料層合板力學(xué)性能分析中最重要的環(huán)節(jié)。傳統(tǒng)的評價(jià)方法往往要么只對剩余強(qiáng)度-開孔尺寸進(jìn)行研究,而忽略復(fù)合材料自身力學(xué)性能分散性顯著的問題;要么只對某一固定尺寸的開孔進(jìn)行多次試驗(yàn),未能全面地評價(jià)含有不同開孔尺寸復(fù)合材料層合板的性能分布和可靠性問題。因此,在開孔復(fù)合材料的強(qiáng)度設(shè)計(jì)問題上大多數(shù)時(shí)候依然采用“見招拆招”的研究方法�；趪鴥�(nèi)對含開孔復(fù)合材料剩余強(qiáng)度研究的現(xiàn)狀與技術(shù)水平,并參考國外先進(jìn)復(fù)合材料可靠性技術(shù)評價(jià)流程,本文將開孔復(fù)合材料的剩余強(qiáng)度評估與復(fù)合材料強(qiáng)度性能分散性評價(jià)結(jié)合起來,提出一種創(chuàng)新性的算法�；谟邢薜氖Ｓ鄰�(qiáng)度試驗(yàn)數(shù)據(jù),本文以有限元仿真計(jì)算的強(qiáng)度為基點(diǎn)擬合的函數(shù)作為復(fù)合材料剩余強(qiáng)度的分析基準(zhǔn),利用貝葉斯理論對含開孔復(fù)合材料層合板的剩余強(qiáng)度進(jìn)行理論上的評估,并給出剩余強(qiáng)度參數(shù)的分布規(guī)律;然后利用馬爾科夫鏈-蒙特卡羅(MCMC)方法對復(fù)合材料層合板的剩余強(qiáng)度進(jìn)行數(shù)值評估,為復(fù)合材料剩余強(qiáng)度概率化評估提供了一種比較普適的求解方法,對復(fù)合材料層合板的開孔剩余強(qiáng)度問題進(jìn)行全面的評價(jià)和表述,給出一個(gè)剩余強(qiáng)度分布規(guī)律關(guān)于開孔尺寸的關(guān)系描述,并對含開孔復(fù)合材料結(jié)構(gòu)的強(qiáng)度百分比分位值以開孔尺寸為自變量的函數(shù)形式進(jìn)行刻畫,從而定性、定量地為含開孔復(fù)合材料承載結(jié)構(gòu)的強(qiáng)度設(shè)計(jì)提供可靠的分析過程和算法依據(jù)。含開孔復(fù)合材料剩余強(qiáng)度分布的研究是飛機(jī)承載部件可靠性分析的基礎(chǔ)課題之一,是后續(xù)研究的必經(jīng)之路。只有在完成這一項(xiàng)成果后,飛機(jī)部件、結(jié)構(gòu)以及整體的安全性、可靠性、損傷容限才能得到全面的分析和保障,飛機(jī)中的部件與結(jié)構(gòu)的強(qiáng)度等力學(xué)性能設(shè)計(jì)才能得到合理而全面的指導(dǎo)。
[Abstract]:Carbon fiber composites (CFRP) have gradually become one of the most important materials in the field of aeronautics and astronautics. From the beginning they were used as minor parts in aircraft, and now they are widely used in the structure of main bearing force, the composite material embodies its important position in industry. However, the structure of aircraft is complex, and because of wiring and maintenance, its bearing parts have to face the problem of opening holes, and the existence of stress concentration phenomenon will greatly weaken the mechanical properties of the bearing parts. At the same time, the mechanical properties of the composites have obvious dispersion, so we need to evaluate the safety and reliability of the components with holes in addition to the correct residual strength evaluation. Therefore, the reasonable reliability, residual strength, damage tolerance design and analysis of the load-bearing components made of composite materials are particularly important in the evaluation of mechanical properties of the load-bearing components in aerospace equipment. The evaluation of residual strength is the most important link in the analysis of mechanical properties of composite laminates with open holes. The traditional evaluation methods usually only study the residual strength and the size of the open hole, but ignore the obvious dispersion of the mechanical properties of the composites. The performance distribution and reliability of composite laminates with different sizes can not be comprehensively evaluated by several tests on a fixed size of the composite laminates. Therefore, in the strength design of porous composite materials, the research method is still adopted in most of the time. Based on the present situation and technical level of domestic research on residual strength of composite materials with open holes, and referring to the evaluation flow of advanced reliability technology of composite materials abroad, In this paper, an innovative algorithm is proposed by combining the residual strength evaluation of the porous composites with the dispersion evaluation of the strength properties of the composites. Based on the finite residual strength test data, this paper uses the function of the finite element simulation calculation as the basic point fitting function as the analysis benchmark of the composite residual strength. Bayesian theory is used to evaluate the residual strength of composite laminates with holes and the distribution of residual strength parameters is given. Then the Markov chain-Monte Carlo (MCMC) method is used to evaluate the residual strength of composite laminates, which provides a general solution for the probabilistic evaluation of composite residual strength. In this paper, the problem of open hole residual strength of composite laminates is comprehensively evaluated and expressed, and the relation between the distribution of residual strength and the size of open hole is given. And the functional form of the strength percentage quantile of the composite structure with open hole size as independent variable is described, so as to qualitatively characterize the strength percentage quantile value of composite structure with open hole. It provides reliable analysis process and algorithm basis for strength design of composite bearing structure with open hole. The study of residual strength distribution of composite materials with open holes is one of the basic problems in reliability analysis of aircraft bearing parts and is the only way to follow up research. Only after this achievement can the safety, reliability and damage tolerance of aircraft components, structures and the whole be fully analyzed and guaranteed. The design of mechanical properties such as the strength of components and structures in aircraft can be guided reasonably and comprehensively.
【學(xué)位授予單位】：哈爾濱工業(yè)大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2017
【分類號】：TB332

【參考文獻(xiàn)】

相關(guān)期刊論文 前5條

1 吳濤;劉喜;李大垣;邢國華;劉伯權(quán);;基于貝葉斯理論的鋼筋混凝土框架中節(jié)點(diǎn)抗剪強(qiáng)度計(jì)算[J];工程力學(xué);2015年03期

2 唐見茂;;航空航天復(fù)合材料發(fā)展現(xiàn)狀及前景[J];航天器環(huán)境工程;2013年04期

3 陳紹杰;;淺談空客A380的復(fù)合材料應(yīng)用[J];高科技纖維與應(yīng)用;2008年04期

4 陳紹杰;;復(fù)合材料技術(shù)與大型飛機(jī)[J];航空學(xué)報(bào);2008年03期

5 杜善義;;先進(jìn)復(fù)合材料與航空航天[J];復(fù)合材料學(xué)報(bào);2007年01期

相關(guān)會議論文 前1條

1 張佐光;李敏;陳紹杰;;飛機(jī)結(jié)構(gòu)用先進(jìn)復(fù)合材料的應(yīng)用與發(fā)展[A];復(fù)合材料——基礎(chǔ)、創(chuàng)新、高效：第十四屆全國復(fù)合材料學(xué)術(shù)會議論文集（上）[C];2006年

相關(guān)重要報(bào)紙文章 前1條

1 孫郁瑤;;C919首飛成功 中國大飛機(jī)夢圓[N];中國工業(yè)報(bào);2017年

相關(guān)博士學(xué)位論文 前3條

1 肖閃閃;飛機(jī)復(fù)合材料結(jié)構(gòu)概率沖擊損傷容限評估方法研究[D];南京航空航天大學(xué);2013年

2 張璐;含分層缺陷復(fù)合材料層合板分層擴(kuò)展行為與數(shù)值模擬研究[D];哈爾濱工業(yè)大學(xué);2012年

3 蘇軍;單向Cf/Al復(fù)合材料缺陷Chirplet參數(shù)表征及強(qiáng)度損傷研究[D];哈爾濱工業(yè)大學(xué);2011年

相關(guān)碩士學(xué)位論文 前4條

1 季晨;基于非局部理論的復(fù)合材料層合板損傷演化研究[D];哈爾濱工業(yè)大學(xué);2016年

2 明慧;復(fù)合材料加工工藝數(shù)據(jù)庫構(gòu)建及數(shù)據(jù)集成[D];大連理工大學(xué);2014年

3 馮康軍;飛機(jī)復(fù)合材料結(jié)構(gòu)損傷容限評定及適航審定技術(shù)研究[D];南京航空航天大學(xué);2010年

4 范海濤;基于概率的飛機(jī)復(fù)合材料層壓板結(jié)構(gòu)設(shè)計(jì)許用值研究[D];上海交通大學(xué);2009年

，

本文編號：2344342