發(fā)布時(shí)間：2018-05-23 09:53

  本文選題：縱列式無(wú)人機(jī) + 旋翼��； 參考：《吉林大學(xué)》2015年博士論文

【摘要】：當(dāng)前,大載荷無(wú)人機(jī)技術(shù)仍屬于國(guó)際前沿科技,只有美國(guó)、英國(guó)、加拿大、德國(guó)、法國(guó)等少數(shù)國(guó)家掌握,而我國(guó)起步較晚,尚處于研發(fā)階段,這與國(guó)際先進(jìn)水平的差距較大。因此,研制性能穩(wěn)定、實(shí)用性強(qiáng)、可應(yīng)用于航空物探領(lǐng)域的大載荷無(wú)人機(jī)是我國(guó)當(dāng)前亟待解決的問(wèn)題�？v列式無(wú)人機(jī)因具有較大的機(jī)身容積、較大的重心可變化范圍以及較強(qiáng)的抗側(cè)風(fēng)能力等優(yōu)點(diǎn),在軍事、民用兩大領(lǐng)域都具有廣闊的應(yīng)用前景。但是,由于縱列式前、后旋翼之間存在一定的重疊區(qū)域,導(dǎo)致兩旋翼之間存在相互的氣動(dòng)干擾,不能像單旋翼那樣單獨(dú)建模,而是需要耦合在一起加以考慮,這給旋翼流場(chǎng)和氣動(dòng)特性的計(jì)算增加了很大難度。為此,本文結(jié)合國(guó)家“863”計(jì)劃項(xiàng)目-“重載荷智能化物探專用無(wú)人直升機(jī)研制”(2013AA063903),開(kāi)展對(duì)縱列式六旋翼大載荷無(wú)人機(jī)旋翼系統(tǒng)流場(chǎng)特性和氣動(dòng)特性的研究工作。論文主要研究?jī)?nèi)容包括：(1)采用CFD方法對(duì)縱列式六旋翼大載荷無(wú)人機(jī)調(diào)節(jié)旋翼的懸停狀態(tài)進(jìn)行了數(shù)值模擬,并對(duì)其流場(chǎng)特性進(jìn)行分析。通過(guò)對(duì)調(diào)節(jié)旋翼試驗(yàn)測(cè)量得出旋翼的基本氣動(dòng)特性,驗(yàn)證了數(shù)值模擬方法的有效性。在此基礎(chǔ)上,對(duì)調(diào)節(jié)旋翼前飛狀態(tài)下的氣動(dòng)特性進(jìn)行分析,分別得出調(diào)節(jié)旋翼的升力、阻力和扭矩隨前傾角、來(lái)流速度、旋翼轉(zhuǎn)速等參數(shù)的變化規(guī)律。(2)運(yùn)用動(dòng)量理論建立了懸停和前飛狀態(tài)下縱列式六旋翼大載荷無(wú)人機(jī)兩副主旋翼的氣動(dòng)力模型,且在模型的建立過(guò)程中考慮了前、后旋翼尾跡之間相互干擾的影響。采用CFD方法對(duì)兩副主旋翼懸停、前飛狀態(tài)下的流場(chǎng)特性和氣動(dòng)特性進(jìn)行計(jì)算分析,并將其與單旋翼數(shù)值模擬結(jié)果進(jìn)行對(duì)比。在此基礎(chǔ)上,分析兩旋翼的縱向間距、軸向間距等參數(shù)對(duì)前、后旋翼氣動(dòng)特性的影響。(3)在分析縱列式六旋翼大載荷無(wú)人機(jī)兩副主旋翼前飛狀態(tài)下流場(chǎng)特性和氣動(dòng)特性的基礎(chǔ)上,采用改進(jìn)的粒子群算法,以兩副主旋翼前飛狀態(tài)下的總升力、總阻力為目標(biāo)函數(shù),以縱向間距、軸向間距和前傾角為約束條件,建立優(yōu)化設(shè)計(jì)模型,對(duì)兩副主旋翼的主要?dú)鈩?dòng)參數(shù)進(jìn)行優(yōu)化。(4)提出了縱列式六旋翼大載荷無(wú)人機(jī)設(shè)計(jì)方案,并對(duì)其動(dòng)力系統(tǒng)、旋翼系統(tǒng)、傳動(dòng)系統(tǒng)以及整機(jī)氣動(dòng)布局進(jìn)行詳細(xì)設(shè)計(jì)。此外,計(jì)算分析了旋翼系統(tǒng)懸停和前飛狀態(tài)下的升阻特性,并采用ANSYS Workbench分析了旋翼系統(tǒng)和減速器齒輪組的振動(dòng)特性。論文創(chuàng)新性成果如下：(1)采用CFD方法對(duì)縱列式六旋翼大載荷無(wú)人機(jī)調(diào)節(jié)旋翼的氣動(dòng)特性進(jìn)行數(shù)值模擬,得出了懸停、前飛狀態(tài)下該旋翼的流場(chǎng)和氣動(dòng)力數(shù)據(jù)。此外,搭建了旋翼氣動(dòng)性能測(cè)試試驗(yàn)臺(tái),通過(guò)試驗(yàn)驗(yàn)證了本文數(shù)值模擬方法的有效性。(2)首次采用CFD方法對(duì)縱列式六旋翼大載荷無(wú)人機(jī)兩副主旋翼懸停、前飛狀態(tài)下的流場(chǎng)特性和氣動(dòng)特性進(jìn)行了計(jì)算分析,并將其與單旋翼數(shù)值模擬結(jié)果進(jìn)行對(duì)比,摸清了影響前、后旋翼氣動(dòng)特性的主要因素—縱向間距、軸向間距、前傾角、來(lái)流速度等參數(shù)與氣動(dòng)特性的關(guān)系。經(jīng)對(duì)比結(jié)果表明,縱向間距、軸向間距和前傾角這三個(gè)參數(shù)對(duì)兩副主旋翼的氣動(dòng)特性具有一定影響,且三者存在耦合作用。(3)針對(duì)縱列式六旋翼大載荷無(wú)人機(jī)設(shè)計(jì)過(guò)程中,縱向間距、軸向間距取值較難確定的難題,提出了一種通過(guò)全局優(yōu)化確定主要?dú)鈩?dòng)參數(shù)最優(yōu)取值的方法。結(jié)果表明,這種方法可以有效地確定最優(yōu)取值,使縱列式六旋翼大載荷無(wú)人機(jī)兩副主旋翼的氣動(dòng)性能得到了顯著改善。(4)提出了縱列式六旋翼大載荷無(wú)人機(jī)的設(shè)計(jì)方案,確定了該無(wú)人機(jī)的氣動(dòng)布局,計(jì)算分析了旋翼系統(tǒng)懸停和前飛狀態(tài)下的升阻特性,證明其可以實(shí)現(xiàn)大載荷的可行性,為我國(guó)自主研發(fā)大載荷無(wú)人機(jī)航空物探飛行平臺(tái)提供了理論基礎(chǔ)。
[Abstract]:At present, the technology of large load UAV still belongs to the frontier science and technology in the world, only in the United States, Britain, Canada, Germany, France and other countries. But our country is late and is still in the stage of research and development, which is far from the international advanced level. Therefore, the development of the large load UAV in the field of Aeronautical geophysical exploration is stable and practical. It is an urgent problem to be solved in China. The column type UAV has the advantages of large body volume, large center of gravity change range and strong anti side wind ability. It has broad application prospects in military and civil two fields. However, there is a certain overlap area between the rear rotor and the two rotor because of the column type. There is mutual aerodynamic interference between each other, which can not be modeled as a single rotor, but need to be coupled together to consider it. This adds to the difficulty of the calculation of the rotor flow field and aerodynamic characteristics. For this reason, this paper combines the national "863" project "heavy load intelligent physical exploration special unmanned helicopter development" (2013AA063903). The research work on the flow field characteristics and aerodynamic characteristics of the large load unmanned aerial vehicle (UAV) rotor system of the column type six rotor is carried out. The main contents of the thesis include: (1) the CFD method is used to simulate the suspension state of the large load unmanned aerial vehicle (UAV) regulating rotor of the column type six rotor, and the flow field characteristics are analyzed. The basic aerodynamic characteristics of the rotor are measured and the effectiveness of the numerical simulation method is verified. On this basis, the aerodynamic characteristics of the adjusting rotor in the forward flight state are analyzed, and the changes of the lift force, the drag and torque with the front tilt angle, the flow velocity, the rotor speed and other parameters are obtained respectively. (2) using the momentum theory to set up the suspension. The aerodynamic model of the two vice main rotor of a large load unmanned aerial vehicle (six rotor) under the state of stop and forward flight, and the influence of mutual interference between the rear rotor wake and the front rotor wake in the establishment of the model, the flow field characteristics and aerodynamic characteristics in the front flight state are calculated and analyzed with the CFD method. The numerical simulation results are compared. On this basis, the longitudinal spacing of the two rotor, the axial spacing and other parameters on the aerodynamic characteristics of the front and rear rotor are analyzed. (3) on the basis of the analysis of the flow field characteristics and aerodynamic characteristics in the front flight state of the two vice main rotor of the column type six rotor large load UAV, the improved particle swarm algorithm is adopted, with two pairs of pairs. The total lift and total drag of the main rotor are the objective function, the optimum design model is set up with the longitudinal spacing, the axial distance and the front angle as the constraint conditions. The main aerodynamic parameters of the two main rotor are optimized. (4) the design scheme of the column type six rotor large load unmanned aircraft is put forward, and the power system, the rotor system and the transmission are also proposed. The system and the pneumatic layout of the whole machine are designed in detail. In addition, the rise resistance characteristics of the rotor system in hovering and forward flight are calculated and analyzed, and the vibration characteristics of the rotor system and the reducer gear group are analyzed with ANSYS Workbench. The innovative results of the paper are as follows: (1) the adjustment of the column type six rotor large load UAV by the CFD method The aerodynamic characteristics of the rotor are numerically simulated, and the flow field and aerodynamic data of the rotor in the forward flight state are obtained. In addition, the rotor aerodynamic performance test rig is built, and the validity of the numerical simulation method is verified by the test. (2) the CFD method is used for the first time of the column type six rotor large load unmanned aerial vehicle (UAV) two main rotor suspension. The flow field characteristics and aerodynamic characteristics in the state of stop and forward flight are calculated and analyzed, and compared with the numerical simulation results of the single rotor, the relationship between the main factors of the aerodynamic characteristics of the rear rotor, such as the longitudinal spacing, the axial distance, the front angle, the velocity of the flow and the aerodynamic characteristics, is found out. The longitudinal spacing is shown by the comparison results. The three parameters of the axial distance and the front angle have a certain influence on the aerodynamic characteristics of the two pair of the main rotor, and the three are coupled. (3) in the design process of the large load unmanned aerial vehicle of the column type six rotor, the longitudinal spacing and the axial spacing are difficult to determine. A global optimization is proposed to determine the optimal parameters of the main aerodynamic parameters. The results show that the method can effectively determine the optimal value and make the aerodynamic performance of the two main rotor of the column six rotor large load UAV significantly improved. (4) the design scheme of the column type six rotor large load UAV is proposed, the aerodynamic layout of the unmanned aerial vehicle is determined, and the rotor system hovering is calculated and analyzed. The rise and drag characteristics of the forward flight show that it can realize the feasibility of large load, and provides a theoretical basis for the independent research and development of China's large load UAV Aero Geophysical flight platform.
【學(xué)位授予單位】：吉林大學(xué)
【學(xué)位級(jí)別】：博士
【學(xué)位授予年份】：2015
【分類號(hào)】：V279
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本文編號(hào)：1924260