發(fā)布時(shí)間：2018-07-10 05:25

  本文選題：水上迫降 + 漂浮特性��； 參考：《武漢理工大學(xué)》2013年碩士論文

【摘要】：伴隨著飛機(jī)跨水域飛行任務(wù)的增多,水上事故的發(fā)生不可避免,機(jī)毀人亡的事故時(shí)有發(fā)生。根據(jù)中國民用航空總局頒布的《中國民用航空規(guī)章第25部：運(yùn)輸類飛機(jī)適航標(biāo)準(zhǔn)》中的要求,需要對(duì)飛機(jī)水上迫降漂浮特性進(jìn)行分析,以確保乘員能安全撤離飛機(jī)并乘上救生船。迫降后飛機(jī)的漂浮特性如何,是降低人員傷亡的核心問題,近年來已經(jīng)成為飛機(jī)設(shè)計(jì)部門和適航認(rèn)證部門研究的重點(diǎn)。 傳統(tǒng)的研究飛機(jī)水上迫降漂浮性能的方法主要有模型實(shí)驗(yàn)、經(jīng)驗(yàn)公式以及理論模型。然而模型實(shí)驗(yàn)成本高、耗時(shí)長,經(jīng)驗(yàn)和理論公式缺乏對(duì)具體問題的復(fù)雜性的反應(yīng)。隨著計(jì)算機(jī)的發(fā)展,采用數(shù)值方法模擬飛機(jī)水上迫降的全過程,對(duì)飛機(jī)迫降性能和漂浮性能進(jìn)行評(píng)價(jià),已經(jīng)成為目前航空界的主流方法。 基于上述原因本文應(yīng)用顯示有限元程序,采用ALE流固耦合的方法對(duì)飛機(jī)水上迫降的漂浮性能進(jìn)行了研究。論文研究的目的是通過對(duì)飛機(jī)不同工況的靜水漂浮做出對(duì)比分析,為飛機(jī)水上漂浮性能的設(shè)計(jì)提供準(zhǔn)則,得到漂浮姿態(tài)、吃水深度等物理量等為飛機(jī)水上迫降的適航認(rèn)證提供數(shù)據(jù)支撐。根據(jù)上述的研究目的和研究重點(diǎn),論文對(duì)以下內(nèi)容進(jìn)行了深入細(xì)致的研究： 1.水上漂浮數(shù)值模型建立的研究,主要包括邊界條件,有限元網(wǎng)格的建立以及流固耦合參數(shù)的選擇。 2.采用顯式動(dòng)力學(xué)方法,引入ALE方法描述流體域,用罰函耦合算法表達(dá)了流體與固體間的耦合作用,對(duì)飛機(jī)靜水漂浮的問題進(jìn)行了模擬研究。 3.針對(duì)飛機(jī)漂浮問題中飛機(jī)下沉過程中的擾動(dòng)問題,通過施加阻尼方式改進(jìn)了此有限元算方法。研究表明通過施加阻尼可以消除飛機(jī)下沉過程中的擾動(dòng)現(xiàn)象。 4.改變飛機(jī)重心位置對(duì)不同工況條件下飛機(jī)漂浮特性進(jìn)行對(duì)比研究,分析不同工況對(duì)飛機(jī)漂浮特性的影響。研究表明前中后重心位置的改變對(duì)飛機(jī)的漂浮穩(wěn)定性和吃水深度影響較小,側(cè)向重心位置的改變對(duì)飛機(jī)吃水深度影響較小,但對(duì)飛機(jī)的穩(wěn)定性有較明顯影響。
[Abstract]:With the increase of aircraft missions across the water, water accidents occur inevitably, aircraft damage accidents occur from time to time. According to the requirements in the regulations on Civil Aviation of China promulgated by the General Administration of Civil Aviation of China, part 25: airworthiness Standards for Transport aircraft, it is necessary to analyze the floating characteristics of aircraft on water. To ensure that the crew can safely evacuate the aircraft and aboard the lifeboat. The floating characteristic of aircraft after forced landing is the core problem to reduce casualties. In recent years, it has become the focus of the aircraft design department and airworthiness certification department. The traditional methods to study the floating performance of aircraft forced landing on water mainly include model experiment, empirical formula and theoretical model. However, the cost of the model experiment is high, the time is long, and the experience and theoretical formula are lack of response to the complexity of the specific problem. With the development of computer, numerical method is used to simulate the whole process of aircraft landing on water, and to evaluate the performance and floating performance of aircraft forced landing has become the mainstream method in aviation field. Based on the above reasons, the floating performance of aircraft forced landing on water was studied by means of ale fluid-solid coupling method using the finite element program. The purpose of this paper is to make a comparative analysis of the aeroplane's hydrostatic floating under different working conditions, and to provide the criteria for the design of the aircraft's floating performance on water, and to obtain the floating attitude. Such physical quantities as draught depth provide data support for airworthiness certification of aircraft landing on water. According to the above research purpose and research focus, the thesis makes a thorough and detailed study on the following contents: 1. The research on the establishment of floating numerical model on water includes boundary conditions, finite element meshes and the choice of fluid-solid coupling parameters. 2. The explicit dynamics method and ale method are introduced to describe the fluid domain. The coupling between fluid and solid is expressed by the penalty function coupling algorithm. The problem of aeroplane floating in still water is simulated and studied. The finite element method is improved by applying damping to the disturbance problem of aircraft sinking in floating problem. Research shows that damping can eliminate the disturbance in the sinking process. 4. 4. The effects of different working conditions on the floating characteristics of aircraft were studied by changing the center of gravity of the aircraft. The results show that the change of the center of gravity has little effect on the floatation stability and the draught depth of the aircraft, while the change of the lateral center of gravity has little effect on the draught depth of the aircraft, but has obvious influence on the stability of the aircraft.
【學(xué)位授予單位】：武漢理工大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2013
【分類號(hào)】：V328;O35

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