旋轉(zhuǎn)機(jī)翼飛機(jī)旋翼模式前飛狀態(tài)干擾氣動特性
發(fā)布時間：2019-01-19 13:59
【摘要】：和傳統(tǒng)直升機(jī)相比,旋轉(zhuǎn)機(jī)翼(CRW)飛機(jī)在旋翼模式前飛時各部件之間存在更為嚴(yán)重的氣動干擾。為了獲得旋轉(zhuǎn)機(jī)翼/機(jī)身/鴨翼/平尾之間的非定常氣動干擾規(guī)律,基于運(yùn)動嵌套網(wǎng)格技術(shù),通過求解三維非定常雷諾平均NavierStokes(URANS)方程,建立了旋翼前飛流場數(shù)值模擬方法。首先對傳統(tǒng)直升機(jī)旋翼/機(jī)身干擾模型進(jìn)行了計(jì)算,驗(yàn)證了方法的可靠性,然后對某旋轉(zhuǎn)機(jī)翼飛機(jī)全機(jī)在旋翼模式前飛狀態(tài)下的非定常流場進(jìn)行了數(shù)值模擬,并對各個氣動部件上的非定常氣動力和力矩的變化進(jìn)行了分析。結(jié)果表明:飛機(jī)在旋翼模式前飛時,機(jī)身部件對旋轉(zhuǎn)機(jī)翼的干擾較弱,在經(jīng)過機(jī)身上方時拉力峰值僅略有增加;旋轉(zhuǎn)機(jī)翼對鴨翼和垂尾干擾較弱,對機(jī)身和平尾干擾較強(qiáng),隨著前飛速度增大,旋轉(zhuǎn)機(jī)翼對平尾的干擾會產(chǎn)生較大的升力損失和抬頭力矩,需要引起重視。計(jì)算結(jié)果為該類飛行器的總體綜合設(shè)計(jì)提供了參考。
[Abstract]:Compared with the traditional helicopter, the rotor wing (CRW) aircraft has more serious aerodynamic interference when it flies in front of the rotor mode. In order to obtain the unsteady aerodynamic interference between the rotating wing / fuselage / duck wing / flat tail, a numerical simulation method for the rotor forward flight flow field is established by solving the three-dimensional unsteady Reynolds mean NavierStokes (URANS) equation based on the moving nested grid technique. Firstly, the traditional helicopter rotor / fuselage interference model is calculated to verify the reliability of the method, and then the unsteady flow field of a rotary-wing aircraft is numerically simulated. The change of unsteady aerodynamic force and torque on each pneumatic component is analyzed. The results show that the interference of the fuselage components to the rotating wing is weak when the aircraft flies in the rotor mode, and the peak value of the tensile force increases only slightly as it passes over the fuselage. The interference of rotating wing to duck wing and vertical tail is weak, and to fuselage and flat tail is stronger. With the increase of forward flight speed, the disturbance of rotating wing to flat tail will cause great lift loss and lift moment, which should be paid more attention to. The results provide a reference for the general design of this kind of aircraft.
【作者單位】： 西北工業(yè)大學(xué)航空學(xué)院;
【基金】：國家自然科學(xué)基金(11372254)~~
【分類號】：V211.52
[Abstract]:Compared with the traditional helicopter, the rotor wing (CRW) aircraft has more serious aerodynamic interference when it flies in front of the rotor mode. In order to obtain the unsteady aerodynamic interference between the rotating wing / fuselage / duck wing / flat tail, a numerical simulation method for the rotor forward flight flow field is established by solving the three-dimensional unsteady Reynolds mean NavierStokes (URANS) equation based on the moving nested grid technique. Firstly, the traditional helicopter rotor / fuselage interference model is calculated to verify the reliability of the method, and then the unsteady flow field of a rotary-wing aircraft is numerically simulated. The change of unsteady aerodynamic force and torque on each pneumatic component is analyzed. The results show that the interference of the fuselage components to the rotating wing is weak when the aircraft flies in the rotor mode, and the peak value of the tensile force increases only slightly as it passes over the fuselage. The interference of rotating wing to duck wing and vertical tail is weak, and to fuselage and flat tail is stronger. With the increase of forward flight speed, the disturbance of rotating wing to flat tail will cause great lift loss and lift moment, which should be paid more attention to. The results provide a reference for the general design of this kind of aircraft.
【作者單位】： 西北工業(yè)大學(xué)航空學(xué)院;
【基金】：國家自然科學(xué)基金(11372254)~~
【分類號】：V211.52
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1 宋亞平;淺談旋翼的防腐維護(hù)[J];航空維修與工程;2004年04期
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本文編號：2411438
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