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  本文關(guān)鍵詞：復(fù)合式無人飛行器試驗(yàn)平臺設(shè)計(jì)與測試　出處：《南京航空航天大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

  更多相關(guān)文章： 無人機(jī) 復(fù)合式 涵道共軸雙旋翼 試驗(yàn)平臺 結(jié)構(gòu)設(shè)計(jì) 飛行測試

【摘要】：近年來,無人機(jī)在軍用和民用領(lǐng)域中受到越來越廣泛的應(yīng)用。由于具有可垂直起降、定點(diǎn)懸停、低空低速性好等優(yōu)點(diǎn),涵道旋翼無人飛行器成為應(yīng)用最廣泛的無人機(jī)之一。本文研究目的是設(shè)計(jì)復(fù)合式涵道共軸雙旋翼無人飛行器試驗(yàn)平臺。根據(jù)飛行器設(shè)計(jì)要求,進(jìn)行飛行器總體結(jié)構(gòu)設(shè)計(jì),闡述了旋翼系統(tǒng)、動力傳動系統(tǒng)、主體梁架以及機(jī)身外形結(jié)構(gòu)等設(shè)計(jì)要求和細(xì)節(jié)。針對共軸雙旋翼飛行器結(jié)構(gòu)要求,提出了上下旋翼對扣的設(shè)計(jì)思想。上下旋翼分別由相互獨(dú)立的動力機(jī)構(gòu)驅(qū)動,采用同步齒形帶動力傳動方式,簡化了動力傳動機(jī)構(gòu)設(shè)計(jì)。分析計(jì)算了旋翼系統(tǒng)動力需求,并通過電動機(jī)驅(qū)動旋翼系統(tǒng)進(jìn)行試驗(yàn)驗(yàn)證,據(jù)此確定發(fā)動機(jī)選型。通過對飛行器的結(jié)構(gòu)受力情況進(jìn)行分析,設(shè)計(jì)了十字形梁架和前三點(diǎn)式起落架結(jié)構(gòu)。飛行器機(jī)身外形采用翼身融合形式設(shè)計(jì),中間嵌有涵道共軸雙旋翼系統(tǒng)。機(jī)身外形采用分塊結(jié)構(gòu)設(shè)計(jì)制作,在確保結(jié)構(gòu)強(qiáng)度的同時方便飛行器安裝、調(diào)試、測試和運(yùn)輸。依據(jù)飛行器飛行性能要求,對飛行器航電飛控系統(tǒng)進(jìn)行配置設(shè)計(jì)。通過進(jìn)行發(fā)動機(jī)功率、旋翼氣動升力以及飛行器地面系留測試試驗(yàn),對涵道共軸雙旋翼飛行器的氣動特性進(jìn)行了分析研究,確定了發(fā)動機(jī)選型、旋翼槳葉結(jié)構(gòu)參數(shù)以及氣動布局設(shè)計(jì),為飛行器設(shè)計(jì)研制提供實(shí)踐依據(jù)。通過本文的研究工作,完成了復(fù)合式涵道共軸雙旋翼無人飛行器總體設(shè)計(jì),并驗(yàn)證了設(shè)計(jì)方案是可行、有效、可靠的。
[Abstract]:In recent years, UAV has been more and more widely used in military and civil fields. It has the advantages of vertical take-off and landing, fixed point hovering, low altitude and low speed, and so on. Culvert rotor unmanned aerial vehicle (UAV) has become one of the most widely used unmanned aerial vehicles (UAVs). The purpose of this study is to design a composite culvert coaxial dual rotor UAV test platform. The design requirements and details of rotor system, power transmission system, main beam frame and fuselage shape structure are described. The design idea of the upper and lower rotor is put forward. The upper and lower rotor is driven by independent power mechanism, and the synchronous gear belt is used to drive the upper and lower rotor. The design of power transmission mechanism is simplified. The dynamic requirements of rotor system are analyzed and calculated, and tested by the motor driven rotor system. According to this, the selection of engine is determined. The cross beam frame and the front three point landing gear structure are designed through the analysis of the structure of the aircraft. The fuselage of the aircraft is designed in the form of wing body fusion. The fuselage is designed and manufactured by block structure, which ensures the strength of the structure and facilitates the installation, debugging, testing and transportation of the aircraft, according to the flight performance requirements of the aircraft. The configuration and design of aircraft avionics flight control system were carried out. The engine power, rotor aerodynamic lift and aircraft ground retention test were carried out. The aerodynamic characteristics of culvert coaxial dual rotor aircraft are analyzed and studied. The engine selection, rotor blade structure parameters and aerodynamic layout design are determined. Through the research work in this paper, the overall design of compound culvert coaxial double rotor unmanned aerial vehicle is completed, and the design scheme is proved to be feasible, effective and reliable.
【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】：2015
【分類號】：V216.8

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本文編號：1410265