本文選題：直升機 + 旋翼　； 參考：《南京航空航天大學(xué)》2016年碩士論文

【摘要】：為研究加裝格尼襟翼旋翼的直升機飛行性能,建立了加裝格尼襟翼旋翼的直升機飛行動力學(xué)模型。采用UH-60A直升機試飛數(shù)據(jù)驗證了計算模型的正確性。在此基礎(chǔ)上分析了樣例直升機加裝格尼襟翼后重量系數(shù)、格尼襟翼高度、沿徑向位置和加裝方式等參數(shù)對旋翼需用功率的影響,以及加裝格尼襟翼后旋翼槳葉剖面迎角分布、旋翼操縱量和機身姿態(tài)角的變化等。研究表明,直升機在重量系數(shù)較大的狀態(tài)下高速前飛時,旋翼加裝格尼襟翼能夠明顯降低直升機的需用功率,且加裝轉(zhuǎn)動格尼襟翼的效果優(yōu)于加裝固定格尼襟翼。功率降低幅值隨格尼襟翼高度的增加先增加后減小。格尼襟翼在槳葉上布置的位置越靠近槳尖,其對需用功率的影響越大。直升機在重量系數(shù)較大的狀態(tài)下高速前飛時,加裝格尼襟翼能夠使旋翼后行側(cè)最大迎角顯著減小。加裝格尼襟翼后旋翼總距和縱橫向周期變距減小。為最大幅度的提升旋翼性能,設(shè)計了格尼襟翼安裝角變化規(guī)律。確定了格尼襟翼安裝角以正弦形式變化的方案,并得到了旋翼性能最優(yōu)時的安裝角變化對應(yīng)正弦函數(shù)的幅值和相位。分析了格尼襟翼安裝角按高階正弦形式變化時的旋翼需用功率變化情況,結(jié)果表明二階和三階正弦形式的變化也能降低旋翼需用功率。
[Abstract]:In order to study the flight performance of the helicopter with the Gini flap rotor, the helicopter flight dynamics model with the Gini flap rotor was established. The validity of the model is verified by the flight test data of UH-60A helicopter. On this basis, the influence of the factors such as the weight coefficient, the height of the Gini flap, the radial position and the mounting mode on the rotor power requirement and the angle of attack distribution of the rotor blade after the installation of the Gini flap are analyzed. Rotor control and fuselage attitude angle change. The results show that when the helicopter flies forward at high speed under the condition of high weight coefficient, the required power of the helicopter can be significantly reduced when the rotor is equipped with the Grigni flap, and the effect of installing the rotated Grigni flap is better than that of the fixed Gini flap. The power reduction amplitude increases first and then decreases with the increase of the height of the Grigni flap. The closer the edge of the blade to the tip of the blade, the greater the influence on the required power. When the helicopter flies forward at high speed under the condition of high weight coefficient, the maximum angle of attack on the rear side of the rotor can be significantly reduced with the addition of the Grigni flap. The rotor total distance and the longitudinal and transverse periodic variation distance are reduced after the installation of the Gini flap. In order to maximize the performance of rotor, the rule of angle change of Gini flap was designed. The scheme that the installation angle of the Grigni flap changes in sinusoidal form is determined and the amplitude and phase of the sinusoidal function corresponding to the installation angle change when the rotor performance is optimized are obtained. The change of rotor power requirement is analyzed when the installation angle of Grigni flap varies according to the higher sinusoidal form. The results show that the change of the second and third order sinusoidal forms can also reduce the rotor power requirement.
【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】：2016
【分類號】：V212.4

【相似文獻】

相關(guān)期刊論文 前6條

1 李化;馬格尼特克公司[J];移動電源與車輛;1995年04期

2 子午;想不到的服務(wù)[J];中小企業(yè)科技;2003年07期

3 李t，

本文編號：1837567