本文選題：共軸雙旋翼傾轉(zhuǎn)旋翼機(jī) + 共軸傾轉(zhuǎn)旋翼��； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：共軸雙旋翼傾轉(zhuǎn)旋翼機(jī)是一款復(fù)合型高速旋翼飛行器,它既具有直升機(jī)垂直起飛和空中懸停的性能,同時(shí)具有固定翼飛行器的高速性能。共軸傾轉(zhuǎn)旋翼能夠在直升機(jī)模式時(shí)作為旋翼使用提供升力,在飛機(jī)模式時(shí),向前傾轉(zhuǎn),作為螺旋槳產(chǎn)生前進(jìn)的推力,共軸雙旋翼傾轉(zhuǎn)旋翼機(jī)在軍、民用方面都具有廣泛的應(yīng)用價(jià)值。本文基于動(dòng)量葉素理論,首先建立了共軸雙旋翼軸流狀態(tài)的性能計(jì)算模型,考慮了共軸雙旋翼存在的氣動(dòng)干擾,分析了拉力系數(shù)、功率系數(shù)以及效率在不同的總距角下,隨軸向來流速度的變化規(guī)律,并與實(shí)驗(yàn)數(shù)據(jù)進(jìn)行比較,驗(yàn)證所建模型的準(zhǔn)確性。在此基礎(chǔ)上,完善軸流狀態(tài)下的雙旋翼氣動(dòng)模型,發(fā)展出共軸雙旋翼傾轉(zhuǎn)狀態(tài)的性能分析方法。然后,分析和計(jì)算了共軸傾轉(zhuǎn)旋翼的槳葉數(shù)、上下旋翼半徑之比、上下旋翼間距、槳葉負(fù)扭轉(zhuǎn)、槳葉尖削比、槳葉安裝角對(duì)共軸傾轉(zhuǎn)旋翼性能的影響,通過綜合優(yōu)化共軸傾轉(zhuǎn)旋翼的參數(shù),得到最優(yōu)的性能。最后,簡要介紹了共軸雙旋翼傾轉(zhuǎn)旋翼機(jī)傾轉(zhuǎn)過渡過程中的氣動(dòng)力變化及操縱方式與策略,闡述了機(jī)翼在不同模式下的變形所遵循的原則,探討了共軸雙旋翼傾轉(zhuǎn)旋翼機(jī)飛行控制系統(tǒng)方案。
[Abstract]:The coaxial twin-rotor tilting rotorcraft is a composite high-speed rotary-wing aircraft, which has not only the performance of helicopter vertical take-off and hovering in the air, but also the high-speed performance of fixed-wing aircraft. The coaxial tilting rotor can be used as a rotor to provide lift in helicopter mode, and in aircraft mode, forward, as the propeller produces forward thrust, and the coaxial double rotor tilting rotor is in the army. The civilian aspect all has the widespread application value. Based on the momentum and leaf element theory, this paper first establishes a performance model for the axial flow state of a coaxial double rotor. The aerodynamic interference of the coaxial double rotor is considered, and the pull coefficient, power coefficient and efficiency are analyzed at different total pitch angles. The accuracy of the model is verified by comparing with the experimental data. On this basis, the aerodynamic model of double rotor under axial flow is improved, and the performance analysis method of coaxial double rotor tilting is developed. Then, the effects of the number of blades, the ratio of the upper and lower rotor radius, the space between the upper and lower rotor, the negative torsion of the blade, the tip cutting ratio of the blade and the installation angle of the blade on the performance of the coaxial tilting rotor are analyzed and calculated. The optimal performance is obtained by synthetically optimizing the parameters of coaxial tilting rotor. In the end, the aerodynamic changes, control modes and strategies during the tilting transition of the coaxial twin-rotor tilting wing are briefly introduced, and the principles of wing deformation in different modes are expounded. In this paper, the flight control system of the coaxial double rotor tilting rotor is discussed.
【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)】：V275.1

【參考文獻(xiàn)】

相關(guān)期刊論文 前6條

1 王強(qiáng);陳銘;王保兵;蘇兵兵;;旋翼幾何參數(shù)對(duì)共軸雙旋翼懸停性能的影響[J];航空動(dòng)力學(xué)報(bào);2014年06期

2 許和勇;葉正寅;;懸停共軸雙旋翼干擾流動(dòng)數(shù)值模擬[J];航空動(dòng)力學(xué)報(bào);2011年02期

3 于世美;鄧彥敏;;共軸式雙旋翼懸停流場的水洞PIV測量[J];航空動(dòng)力學(xué)報(bào);2007年11期

4 童自力，，孫茂;共軸式雙旋翼氣動(dòng)力特性的計(jì)算研究[J];航空學(xué)報(bào);1999年04期

5 唐正飛,李鋒,高正,梅衛(wèi)勝;用三維激光多譜勒測速儀對(duì)共軸雙旋翼懸停流場的測定[J];流體力學(xué)實(shí)驗(yàn)與測量;1998年01期

6 童自力,孫茂;共軸式雙旋翼流動(dòng)的 N-S 方程模擬[J];航空學(xué)報(bào);1998年01期

相關(guān)博士學(xué)位論文 前1條

1 曾麗蘭;基于H_∞回路成形的無人直升機(jī)非脆弱魯棒飛行控制研究[D];南京航空航天大學(xué);2006年

相關(guān)碩士學(xué)位論文 前1條

1 詹志莉;基于回路成形的控制器設(shè)計(jì)[D];天津大學(xué);2005年

本文編號(hào)：1966651