民机维修大纲结构疲劳损伤评估方法研究
发布时间：2018-11-14 14:01
【摘要】：民用飞机的维修,是航空公司保证飞机安全、维持飞机持续适航以及航空公司正常营运的基本手段和重要方式,同时也是民用航空运输业和航空工业发展的重要保障。飞机结构疲劳损伤的评估是制订飞机结构维修大纲的关键问题之一,在我国研制拥有自主知识产权民用飞机的今天,开展结构疲劳损伤评估研究具有非常重要的现实意义。本文以工程实践为背景,重点对飞机维修大纲制订过程中疲劳损伤的评估进行研究,具体包括以下三方面的内容:1、分析疲劳损伤可检性的评估方法,提出采用模糊层次分析法确定疲劳损伤目视可检裂纹尺寸,该方法可有效地确定各影响因素的权重,避免层次分析法主观性太强的缺点,使得最后确定的检查方式和维修任务更加合理;2、针对维修大纲中疲劳损伤觉察可靠性的评估,研究了飞机结构疲劳强度损伤容限额定值评价方法的机理,详细分析了DTR法的评定步骤和在实际维修大纲制定中的应用,提出采用DTR法来评估疲劳裂纹觉察可靠性,并应用DTR分析方法对某结构细节在不同检查间隔、不同机队裂纹数下的疲劳损伤检查进行了评估;3、针对适航规章新的要求,对广布疲劳损伤评定的内容和程序进行了分析,研究如何应用有限元分析软件Franc2D/L对结构疲劳裂纹扩展进行分析,基于该软件对含多位置损伤的单孔、双孔以及多孔有限宽板进行了裂纹扩展分析,得出不同损伤模型下的裂纹扩展寿命曲线,计算结果表明影响含MSD有限宽板的裂纹扩展的因素有铆钉孔间距、临近裂纹的长度及边界条件。为制定结构维修大纲过程中对飞机蒙皮铆钉孔广布疲劳损伤的评估提供具有实际应用的结论。
[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.
【学位授予单位】：中国民航大学
【学位级别】：硕士
【学位授予年份】：2014
【分类号】：V267
本文编号：2331362
[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.
【学位授予单位】：中国民航大学
【学位级别】：硕士
【学位授予年份】：2014
【分类号】：V267
【引证文献】
相关硕士学位论文 前1条
1 童帅;民机结构维修间隔与飞机利用率匹配方法研究[D];中国民航大学;2015年
，本文编号：2331362
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