旋转机翼飞机旋翼模式前飞状态干扰气动特性
发布时间：2019-01-19 13:59
【摘要】：和传统直升机相比,旋转机翼(CRW)飞机在旋翼模式前飞时各部件之间存在更为严重的气动干扰。为了获得旋转机翼/机身/鸭翼/平尾之间的非定常气动干扰规律,基于运动嵌套网格技术,通过求解三维非定常雷诺平均NavierStokes(URANS)方程,建立了旋翼前飞流场数值模拟方法。首先对传统直升机旋翼/机身干扰模型进行了计算,验证了方法的可靠性,然后对某旋转机翼飞机全机在旋翼模式前飞状态下的非定常流场进行了数值模拟,并对各个气动部件上的非定常气动力和力矩的变化进行了分析。结果表明:飞机在旋翼模式前飞时,机身部件对旋转机翼的干扰较弱,在经过机身上方时拉力峰值仅略有增加;旋转机翼对鸭翼和垂尾干扰较弱,对机身和平尾干扰较强,随着前飞速度增大,旋转机翼对平尾的干扰会产生较大的升力损失和抬头力矩,需要引起重视。计算结果为该类飞行器的总体综合设计提供了参考。
[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.
【作者单位】： 西北工业大学航空学院;
【基金】：国家自然科学基金(11372254)~~
【分类号】：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.
【作者单位】： 西北工业大学航空学院;
【基金】：国家自然科学基金(11372254)~~
【分类号】：V211.52
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