旋轉(zhuǎn)機翼飛機旋翼模式前飛狀態(tài)干擾氣動特性
發(fā)布時間：2019-01-19 13:59
【摘要】：和傳統(tǒng)直升機相比,旋轉(zhuǎn)機翼(CRW)飛機在旋翼模式前飛時各部件之間存在更為嚴重的氣動干擾。為了獲得旋轉(zhuǎn)機翼/機身/鴨翼/平尾之間的非定常氣動干擾規(guī)律,基于運動嵌套網(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)直升機旋翼/機身干擾模型進行了計算,驗證了方法的可靠性,然后對某旋轉(zhuǎn)機翼飛機全機在旋翼模式前飛狀態(tài)下的非定常流場進行了數(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行了分析。結(jié)果表明:飛機在旋翼模式前飛時,機身部件對旋轉(zhuǎn)機翼的干擾較弱,在經(jīng)過機身上方時拉力峰值僅略有增加;旋轉(zhuǎn)機翼對鴨翼和垂尾干擾較弱,對機身和平尾干擾較強,隨著前飛速度增大,旋轉(zhuǎn)機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。計算結(jié)果為該類飛行器的總體綜合設(shè)計提供了參考。
[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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