本文關(guān)鍵詞： 接觸 有限元 疲勞裂紋萌生壽命 疲勞裂紋擴(kuò)展壽命 剩余壽命 動力學(xué)特性　出處：《南京航空航天大學(xué)》2012年碩士論文　論文類型：學(xué)位論文

【摘要】：接觸聯(lián)接結(jié)構(gòu)廣泛用于各類機(jī)械結(jié)構(gòu)中，例如螺栓聯(lián)接結(jié)構(gòu)、鉚釘聯(lián)接結(jié)構(gòu)、銷釘聯(lián)接結(jié)構(gòu)等。由于聯(lián)接部位有接觸的存在，并且這些聯(lián)接結(jié)構(gòu)通常處于惡劣的工作環(huán)境，經(jīng)常會出現(xiàn)疲勞失效問題；近年來由于復(fù)雜結(jié)構(gòu)的大型化和柔性化，使聯(lián)接部動力學(xué)特性對整機(jī)性能的影響顯得更加重要。本文通過有限元仿真對吊耳螺栓聯(lián)接結(jié)構(gòu)的失效故障預(yù)報(bào)和飛機(jī)蒙皮與長桁鉚接結(jié)構(gòu)的動力學(xué)特性進(jìn)行了研究，探討了在復(fù)合載荷作用下并考慮零件表面之間的接觸現(xiàn)象時，結(jié)構(gòu)件的疲勞裂紋產(chǎn)生以及擴(kuò)展過程和速度，從而提高了結(jié)構(gòu)的失效故障預(yù)報(bào)的可靠性，比較了傳統(tǒng)不考慮接觸現(xiàn)象時的結(jié)果，發(fā)現(xiàn)接觸現(xiàn)象對裂紋擴(kuò)展速度以及模態(tài)參數(shù)都有不可忽視的影響，并采用灰色模型對考慮接觸時結(jié)構(gòu)的剩余壽命進(jìn)行了預(yù)測。 建立了吊耳螺栓聯(lián)接結(jié)構(gòu)有限元模型，通過應(yīng)力分析預(yù)報(bào)出故障危險(xiǎn)點(diǎn)，并分析了預(yù)緊力和剪力對危險(xiǎn)點(diǎn)應(yīng)力的影響，最后計(jì)算了考慮接觸和不考慮接觸的疲勞裂紋萌生壽命，發(fā)現(xiàn)接觸對疲勞裂紋萌生壽命有一定影響。 建立了含裂紋的吊耳螺栓聯(lián)接結(jié)構(gòu)有限元模型，分析了接觸、裂紋深度以及橢圓裂紋長短半軸之比對應(yīng)力強(qiáng)度因子的影響，，分析了接觸對裂紋擴(kuò)展速率的影響，并計(jì)算了考慮接觸和不考慮接觸的疲勞裂紋擴(kuò)展壽命，發(fā)現(xiàn)接觸對裂紋擴(kuò)展速率和疲勞裂紋擴(kuò)展壽命有一定影響。 提出了吊耳螺栓聯(lián)接結(jié)構(gòu)的剩余壽命預(yù)測流程，利用新陳代謝灰色預(yù)測模型預(yù)測了應(yīng)力強(qiáng)度因子隨裂紋深度變化值，進(jìn)一步計(jì)算了裂紋擴(kuò)展速率隨裂紋深度變化值，最后計(jì)算了吊耳螺栓聯(lián)接結(jié)構(gòu)的疲勞剩余壽命。 建立了飛機(jī)蒙皮與長桁鉚接聯(lián)接有限元模型，對系統(tǒng)進(jìn)行模態(tài)分析，然后在不同工況下對系統(tǒng)進(jìn)行瞬態(tài)動力學(xué)分析，研究了接觸和預(yù)緊力對系統(tǒng)固有頻率等動態(tài)特性的影響，發(fā)現(xiàn)實(shí)際的接觸情況對整個系統(tǒng)的動力學(xué)特性影響顯著。
[Abstract]:Contact connection structure is widely used in various mechanical structures, such as bolt connection structure, rivet connection structure, pin connection structure, etc. And these connection structures are usually in a bad working environment, often appear fatigue failure problem; In recent years, due to the large-scale and flexible of complex structures. In this paper, the finite element simulation is used to predict the failure of hoisting bolt connection structure and the dynamic characteristics of aircraft skin and long truss riveting structure. Research. In this paper, the fatigue crack generation, propagation process and speed of structural parts under the action of composite load and considering the contact phenomenon between parts surfaces are discussed, thus improving the reliability of structural failure prediction. It is found that the contact phenomenon has an important effect on the crack growth speed and modal parameters. The residual life of the structure considering contact is predicted by grey model. The finite element model of bolt connection structure is established, and the fault danger point is predicted by stress analysis, and the influence of preload force and shear force on the stress of dangerous point is analyzed. Finally, the fatigue crack initiation life with and without contact is calculated, and it is found that contact has some influence on the fatigue crack initiation life. The finite element model of the bolt connection structure with cracks is established, and the effects of contact, crack depth and the ratio of elliptical crack length and half axis on the stress intensity factor are analyzed. The influence of contact on crack growth rate is analyzed, and the fatigue crack growth life with and without contact is calculated. It is found that contact has some influence on crack growth rate and fatigue crack growth life. The residual life prediction process of the bolt connection structure is presented and the stress intensity factor with crack depth is predicted by the metabolic grey prediction model. The variation of crack growth rate with crack depth is further calculated. Finally, the fatigue residual life of suspension bolt connection structure is calculated. The finite element model of aircraft skin and long truss riveting connection is established. The modal analysis of the system is carried out, and the transient dynamics of the system is analyzed under different working conditions. The effects of contact and preloading forces on the dynamic characteristics of the system such as natural frequency are studied. It is found that the actual contact conditions have a significant effect on the dynamic characteristics of the whole system.
【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】：2012
【分類號】：TH131

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