發(fā)布時間：2018-11-14 14:01

【摘要】：民用飛機(jī)的維修,是航空公司保證飛機(jī)安全、維持飛機(jī)持續(xù)適航以及航空公司正常營運(yùn)的基本手段和重要方式,同時也是民用航空運(yùn)輸業(yè)和航空工業(yè)發(fā)展的重要保障。飛機(jī)結(jié)構(gòu)疲勞損傷的評估是制訂飛機(jī)結(jié)構(gòu)維修大綱的關(guān)鍵問題之一,在我國研制擁有自主知識產(chǎn)權(quán)民用飛機(jī)的今天,開展結(jié)構(gòu)疲勞損傷評估研究具有非常重要的現(xiàn)實(shí)意義。本文以工程實(shí)踐為背景,重點(diǎn)對飛機(jī)維修大綱制訂過程中疲勞損傷的評估進(jìn)行研究,具體包括以下三方面的內(nèi)容:1、分析疲勞損傷可檢性的評估方法,提出采用模糊層次分析法確定疲勞損傷目視可檢裂紋尺寸,該方法可有效地確定各影響因素的權(quán)重,避免層次分析法主觀性太強(qiáng)的缺點(diǎn),使得最后確定的檢查方式和維修任務(wù)更加合理;2、針對維修大綱中疲勞損傷覺察可靠性的評估,研究了飛機(jī)結(jié)構(gòu)疲勞強(qiáng)度損傷容限額定值評價方法的機(jī)理,詳細(xì)分析了DTR法的評定步驟和在實(shí)際維修大綱制定中的應(yīng)用,提出采用DTR法來評估疲勞裂紋覺察可靠性,并應(yīng)用DTR分析方法對某結(jié)構(gòu)細(xì)節(jié)在不同檢查間隔、不同機(jī)隊(duì)裂紋數(shù)下的疲勞損傷檢查進(jìn)行了評估;3、針對適航規(guī)章新的要求,對廣布疲勞損傷評定的內(nèi)容和程序進(jìn)行了分析,研究如何應(yīng)用有限元分析軟件Franc2D/L對結(jié)構(gòu)疲勞裂紋擴(kuò)展進(jìn)行分析,基于該軟件對含多位置損傷的單孔、雙孔以及多孔有限寬板進(jìn)行了裂紋擴(kuò)展分析,得出不同損傷模型下的裂紋擴(kuò)展壽命曲線,計(jì)算結(jié)果表明影響含MSD有限寬板的裂紋擴(kuò)展的因素有鉚釘孔間距、臨近裂紋的長度及邊界條件。為制定結(jié)構(gòu)維修大綱過程中對飛機(jī)蒙皮鉚釘孔廣布疲勞損傷的評估提供具有實(shí)際應(yīng)用的結(jié)論。
[Abstract]:The maintenance of civil aircraft is the basic means and important way for the airlines to ensure the safety of the aircraft, to maintain the airworthiness of the aircraft and to maintain the normal operation of the airlines. At the same time, it is also an important guarantee for the development of the civil aviation transportation industry and the aviation industry. The evaluation of aircraft structure fatigue damage is one of the key problems in formulating the aircraft structure maintenance outline. It is of great practical significance to carry out the structural fatigue damage assessment research in our country with the development of civil aircraft with independent intellectual property rights. Based on engineering practice, this paper focuses on the evaluation of fatigue damage in the course of aircraft maintenance outline formulation, including the following three aspects: 1. The evaluation method of fatigue damage detectability is analyzed. A fuzzy analytic hierarchy process (FAHP) is proposed to determine the visible crack size of fatigue damage. This method can effectively determine the weight of each factor and avoid the disadvantage that AHP is too subjective. Make the final determination of inspection methods and maintenance tasks more reasonable; 2. In view of the reliability evaluation of fatigue damage detection in maintenance outline, the mechanism of evaluation method for fatigue strength damage tolerance rating of aircraft structure is studied, and the evaluation steps of DTR method and its application in drawing up actual maintenance outline are analyzed in detail. The DTR method is used to evaluate the fatigue crack detection reliability, and the DTR analysis method is applied to evaluate the fatigue damage of a structure with different inspection intervals and different fleet cracks. 3. According to the new requirements of airworthiness regulations, the contents and procedures of wide-spread fatigue damage assessment are analyzed, and how to use finite element analysis software Franc2D/L to analyze fatigue crack propagation of structures is studied. Based on the software, the crack propagation of single hole, double hole and porous finite wide plate with multi-position damage is analyzed, and the crack growth life curves under different damage models are obtained. The results show that the factors affecting the crack growth of the plate with MSD are rivet hole spacing, the length of the adjacent crack and the boundary conditions. A practical application conclusion is provided for the assessment of the extensive fatigue damage of rivet holes in aircraft skin during the course of making the structural maintenance outline.
【學(xué)位授予單位】：中國民航大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2014
【分類號】：V267

【引證文獻(xiàn)】

相關(guān)碩士學(xué)位論文 前1條

1 童帥;民機(jī)結(jié)構(gòu)維修間隔與飛機(jī)利用率匹配方法研究[D];中國民航大學(xué);2015年

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本文編號：2331362