本文選題：傾轉(zhuǎn)旋翼機(jī) + 非定常干擾特性�。� 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：傾轉(zhuǎn)旋翼機(jī)具有比常規(guī)直升機(jī)高得多的前飛速度和續(xù)航能力,又具有常規(guī)固定翼飛機(jī)所不具備的垂直起降和懸停能力,能滿足多種飛行任務(wù)的需要,因此近年來(lái)無(wú)論在軍用或民用方面對(duì)傾轉(zhuǎn)旋翼機(jī)的需求越來(lái)越大。然而,作為介于直升機(jī)和固定翼之間的一種機(jī)型,傾轉(zhuǎn)旋翼機(jī)具有比兩者更為復(fù)雜的氣動(dòng)干擾現(xiàn)象,嚴(yán)重影響了傾轉(zhuǎn)旋翼機(jī)的氣動(dòng)性能。因此,開(kāi)展傾轉(zhuǎn)旋翼機(jī)復(fù)雜氣動(dòng)干擾的分析及氣動(dòng)優(yōu)化設(shè)計(jì)的研究具有重要的理論和實(shí)際意義。本文基于非結(jié)構(gòu)混合網(wǎng)格系統(tǒng),提出并建立了用于傾轉(zhuǎn)旋翼機(jī)氣動(dòng)干擾特性分析的非定常動(dòng)量源方法,并應(yīng)用建立的數(shù)值模擬方法分別開(kāi)展傾轉(zhuǎn)旋翼機(jī)多狀態(tài)氣動(dòng)干擾流場(chǎng)分析、傾轉(zhuǎn)旋翼機(jī)結(jié)構(gòu)/氣動(dòng)參數(shù)的影響特性分析、傾轉(zhuǎn)旋翼機(jī)多狀態(tài)氣動(dòng)優(yōu)化設(shè)計(jì)。主要研究工作包括以下幾個(gè)方面:第一章,針對(duì)傾轉(zhuǎn)旋翼機(jī)復(fù)雜的氣動(dòng)干擾問(wèn)題,分析了國(guó)內(nèi)外在傾轉(zhuǎn)旋翼機(jī)流場(chǎng)數(shù)值模擬方法、動(dòng)量源方法以及傾轉(zhuǎn)旋翼機(jī)氣動(dòng)外形優(yōu)化設(shè)計(jì)研究方面的技術(shù)現(xiàn)狀及難點(diǎn),并指出了采用耦合新型非定常動(dòng)量源模型的數(shù)值模擬方法對(duì)傾轉(zhuǎn)旋翼機(jī)非定常流場(chǎng)及氣動(dòng)特性數(shù)值模擬的必要性和重要意義。第二章,為了充分捕捉附面層內(nèi)粘性流動(dòng)對(duì)傾轉(zhuǎn)旋翼機(jī)氣動(dòng)特性的影響,同時(shí)考慮多種飛行狀態(tài)特點(diǎn),構(gòu)建了底層三棱柱網(wǎng)格—外層四面體網(wǎng)格相結(jié)合的非結(jié)構(gòu)混合網(wǎng)格系統(tǒng)。為了滿足非定常動(dòng)量源計(jì)算的需要,將非結(jié)構(gòu)混合網(wǎng)格、二維翼型網(wǎng)格和笛卡爾搜索網(wǎng)格相耦合,建立了一套傾轉(zhuǎn)旋翼機(jī)干擾流場(chǎng)數(shù)值模擬的網(wǎng)格生成方法,并給出了多種網(wǎng)格生成結(jié)果。第三章,在建立的網(wǎng)格生成方法的基礎(chǔ)上,構(gòu)建了適用于不同飛行狀態(tài)下傾轉(zhuǎn)旋翼機(jī)非定常流場(chǎng)數(shù)值模擬方法。為了兼顧傾轉(zhuǎn)旋翼機(jī)干擾流場(chǎng)的模擬精度和效率,首先,提出了一種介于貼體CFD方法與傳統(tǒng)動(dòng)量源方法之間的非定常動(dòng)量源方法;然后,將Navier-Stokes方程作為控制方程,湍流模型選取了一方程S-A模型,采用了雙時(shí)間推進(jìn)方法;并引入OpenMP并行加速技術(shù)。在此基礎(chǔ)上,通過(guò)不同模型旋翼流場(chǎng)的算例計(jì)算,驗(yàn)證了本文方法的有效性,同時(shí)對(duì)比反映了非定常動(dòng)量源方法具有較好的計(jì)算精度和效率。第四章,為了揭示傾轉(zhuǎn)旋翼機(jī)的非定常氣動(dòng)干擾現(xiàn)象,在上述分析方法基礎(chǔ)上,對(duì)懸停、前飛(直升機(jī)模式、飛機(jī)模式)以及過(guò)渡狀態(tài)下傾轉(zhuǎn)旋翼機(jī)的全機(jī)氣動(dòng)干擾流場(chǎng)進(jìn)行了模擬。細(xì)致分析了懸停狀態(tài)下傾轉(zhuǎn)旋翼機(jī)特有的“噴泉效應(yīng)”、不同前飛模式下干擾程度和方式的差別以及不同過(guò)渡狀態(tài)下的傾轉(zhuǎn)旋翼機(jī)氣動(dòng)特性變化特征等,獲得了多狀態(tài)下傾轉(zhuǎn)旋翼機(jī)非定常干擾流場(chǎng)的特性。第五章,為了獲得不同結(jié)構(gòu)/氣動(dòng)參數(shù)對(duì)傾轉(zhuǎn)旋翼機(jī)干擾流場(chǎng)的影響特性,針對(duì)不同飛行狀態(tài),分別開(kāi)展了旋翼/機(jī)翼間距、機(jī)翼襟翼角、旋翼轉(zhuǎn)向及尾翼構(gòu)型對(duì)全機(jī)流場(chǎng)的干擾影響,獲得了相應(yīng)的參數(shù)影響規(guī)律。并進(jìn)一步分析了各部件對(duì)機(jī)翼的氣動(dòng)干擾方式和程度,為進(jìn)行傾轉(zhuǎn)旋翼機(jī)多目標(biāo)、多狀態(tài)的氣動(dòng)優(yōu)化打下了基礎(chǔ)。第六章,將CFD方法和代理模型方法相結(jié)合,建立了一套適用于傾轉(zhuǎn)旋翼機(jī)氣動(dòng)外形綜合優(yōu)化的高效優(yōu)化設(shè)計(jì)方法。為了提高傾轉(zhuǎn)旋翼機(jī)的運(yùn)輸性能,以降低干擾狀態(tài)下懸停狀態(tài)的機(jī)身增重和前飛狀態(tài)下的阻力為優(yōu)化目標(biāo),選取機(jī)翼后掠角、翼型配置等作為設(shè)計(jì)參數(shù),對(duì)懸停、前飛狀態(tài)下的傾轉(zhuǎn)旋翼機(jī)進(jìn)行了綜合優(yōu)化設(shè)計(jì),獲得了傾轉(zhuǎn)旋翼機(jī)先進(jìn)氣動(dòng)外形的設(shè)計(jì)結(jié)果。
[Abstract]:The tiltilla has a much higher speed and endurance than the conventional helicopter. It also has the vertical landing and hovering capacity that the conventional fixed wing aircraft does not have, and can meet the needs of various flight tasks. Therefore, in recent years, the demand for the tilting rotor is increasing both in military and civil aspects. A type of aircraft between the aircraft and the fixed wing, the tilting rotor has more complex aerodynamic interference than both, seriously affecting the aerodynamic performance of the tilting rotor. Therefore, it is of great theoretical and practical significance to carry out the analysis of the complex aerodynamic interference and the aerodynamic optimization design of the tilterer. The non steady momentum source method for the aerodynamic interference characteristic analysis of the tilting rotor machine is proposed and established. The numerical simulation method is used to analyze the multi state aerodynamic interference flow field of the tilting rotor machine, the influence characteristic analysis of the structure / aerodynamic parameters of the tilting rotor machine, and the multi state aerodynamic optimization design of the tilting rotor machine. The main research work includes the following aspects: in the first chapter, in view of the complicated aerodynamic interference of the tilting rotor machine, the numerical simulation method of the flow field of the tilting rotor machine, the momentum source method and the aerodynamic configuration optimization design of the tilting rotor machine are analyzed. The numerical simulation of the momentum source model is necessary and important for the unsteady flow field and aerodynamic characteristics of the tilting rotor machine. In the second chapter, in order to fully capture the influence of the viscous flow in the surface layer on the aerodynamic characteristics of the tilterer, and considering the special points of a variety of flight States, the bottom three prism grid and the outer layer are constructed. In order to meet the needs of the unsteady momentum source calculation, the unstructured hybrid grid, the two-dimensional airfoil grid and the Descartes search grid are coupled to meet the needs of the unsteady momentum source calculation. A set of grid generation methods for the numerical simulation of the disturbance flow field of the tilting rotor machine is established, and the results of various grid generation are given. Third chapters, On the basis of the established grid generation method, a numerical simulation method for the unsteady flow field of the tilting rotor machine for different flight states is constructed. In order to give consideration to the simulation accuracy and efficiency of the interfering flow field of the tilting rotor, a non constant momentum source method between the body fitted CFD method and the traditional dynamic source method is proposed. The Navier-Stokes equation is used as the control equation, the turbulence model selects a equation S-A model, adopts the double time propulsion method, and introduces the OpenMP parallel acceleration technique. On this basis, the effectiveness of the method is verified by calculating the flow field of different models of the rotor, and the comparison reflects that the non steady momentum source method has a comparison. Good calculation accuracy and efficiency. In the fourth chapter, in order to reveal the unsteady aerodynamic interference of the tilting rotor machine, on the basis of the above analysis method, the whole aerodynamic disturbance flow field of the hovering, forward flight (helicopter mode, aircraft mode) and the transition state lower tilting rotor is simulated. The hovering rotor machine is carefully analyzed. The special "fountain effect", the difference of the interference degree and mode in the forward flight mode and the characteristics of the aerodynamic characteristics of the tilting rotor machine under different transition states, the characteristics of the unsteady disturbance flow field of the multi state tilting rotor machine are obtained. In the fifth chapter, the interference flow field of the tilting rotor machine with different structure / aerodynamic parameters is obtained. The influence of the rotor / wing spacing, the wing flap angle, the wing steering and the tail wing configuration on the whole flow field is carried out in different flight conditions, and the corresponding parameter influence rules are obtained. Furthermore, the aerodynamic interference mode and degree of each component to the wing are further analyzed, in order to carry out the multi state of the tilting rotor machine and multi state. The sixth chapter, combining the CFD method with the agent model method, establishes a set of efficient optimization design method for the comprehensive optimization of the aerodynamic shape of the tilting rotor machine. In order to improve the transport performance of the tilting rotor machine, the weight gain and the resistance in the forward flight state of the hovering state are reduced. To optimize the target, select the wing sweep angle and the airfoil configuration as the design parameters, the optimization design of the tilting rotor in the hovering and forward flight is carried out, and the design results of the advanced aerodynamic shape of the tilting rotor are obtained.

【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類號(hào)】：V211.52

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