Analysis of aerodynamic interaction characteristics of tilting wing aircraft in helicopter mode
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摘要:
针对多旋翼倾转机翼飞行器，开展了直升机模式机翼/旋翼气动干扰计算分析。基于CFD方法建立了适用于多旋翼倾转机翼飞行器气动干扰分析的计算模型，然后对直升机模式时悬停和前飞状态下的机翼/旋翼气动干扰进行了数值计算，重点分析了气动干扰对机翼气动特性的影响，并进一步研究了襟翼及副翼偏转对机翼/旋翼气动干扰特性的影响规律。结果表明：悬停状态，受旋翼尾流影响，机翼产生较大的后向力，约占旋翼总拉力的5.4%；悬停时襟翼及副翼偏转可实现纵向和航向的有效操纵，前飞时通过襟翼及副翼上偏可以使机翼后向力降低约30%，从而提高最大前飞速度。
Abstract:The wing/rotor aerodynamic interference of multi-rotor tilting wing aircraft in helicopter mode was analyzed. Computational model for the aerodynamic interference analysis was established based on CFD method. The aerodynamic interference of the wing/rotor in hover and forward flight was numerically calculated, the influence of aerodynamic interference on the aerodynamic characteristics of the wing was analyzed, and the influence law of flap and aileron deflections was further studied. The results showed that, under the influence of rotor wake, the wing generated a large backward force, accounting for 5.4% of the total rotor force. The flap and aileron deflections during hovering can achieve effective longitudinal and heading maneuvers, and the flap and aileron up deflections during forward flight can reduce the backward wing force by 30%, thereby increasing the maximum forward flight speed.
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图 6 前进比为0.7时，机翼截面压力对比
Figure 6. Comparison of wing section pressure with advance ratio being 0.7
图 7 机翼升力系数计算与试验值对比
Figure 7. Comparison of calculated and experimental wing lift coefficients
图 8 螺旋桨拉力系数计算与试验值对比
Figure 8. Comparison of calculated and experimental propeller tension coefficients
图 11 直升机模式下的多旋翼倾转机翼飞行器侧视图
Figure 11. Side view of multi-rotor tilting wing aircraft in helicopter mode
图 13 机翼水平力随网格数量变化曲线
Figure 13. Curve of wing horizontal force varying with the number of grids
图 14 机翼表面压力分布及流向截面速度等值线图
Figure 14. Velocity distribution in cutting plane of x=0.05 m and pressure contour in wing surface
图 15 机翼上方约0.2倍弦长截面的垂向速度云图及表面流线图
Figure 15. Vertical velocity contour and streamlines in cutting plane at about 0.2 chord length in front of the wing
图 16 机翼剖面水平力系数沿展向分布
Figure 16. Section horizontal force coefficient distribution along wing span
图 17 过机翼展向截面压力分布及流线图
Figure 17. Pressure contour and streamlines in cutting plane crossing wing
图 18 机翼垂向力和水平力随襟副翼偏转角度的变化规律
Figure 18. Variation of wing vertical and horizontal force with flap and aileron deflection angle
图 19 机翼偏航力矩与旋翼扭矩的比随襟副翼偏转角的变化规律
Figure 19. Ratio of wing yaw moment to rotor torque varies with flap and aileron deflection angle
图 20 机翼水平力与旋翼拉力比随前飞速度的变化规律
Figure 20. Ratio of wing horizontal force to rotor thrust varies with forward flying speed
图 21 孤立机翼状态，过旋翼中心展向截面压力分布及流线图（前飞速度为30 m/s）
Figure 21. Pressure contour and streamlines in cutting plane crossing rotor center at isolated wing condition（flight speed of 30 m/s）
图 22 机翼/旋翼干扰状态，不同前飞速度下过旋翼中心展向截面压力分布及流线图
Figure 22. Pressure contour and streamlines in cutting plane crossing rotor center at different flight speeds under aerodynamic interaction
图 23 不同前飞速度下，机翼剖面水平力系数沿展向分布
Figure 23. Section horizontal force coefficient along wing span at different flight speeds
图 24 过机翼50%弦长位置截面速度分布及流线图（前飞速度为30 m/s）
Figure 24. Velocity contour and streamlines in cutting plane crossing half wing chord （flight speed of 30 m/s）
图 25 机翼水平力和垂向力随襟副翼偏转角变化规律（前飞速度为30 m/s）
Figure 25. Variation of wing horizontal force and vertical force with flap and aileron deflection angle （flight speed of 30 m/s）
图 26 y=3 m展向截面压力分布及流线图
Figure 26. Pressure contour and streamlines in cutting plane at position of y=3 m
表 1 机翼/螺旋桨干扰模型参数
Table 1. Wing/propeller interference model parameters
参数 数值 风速/（m/s） 40 螺旋桨直径/m 0.237 桨叶片数 4 桨距（75%桨叶半径位置）/（°） 23.9 机翼半展长/m 0.292 机翼弦长/m 0.24 机翼安装角/（°） 0 襟翼角度/（°） 10 机翼翼型 NACA 642A015 
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表 2 倾转机翼飞行器干扰计算模型主要参数
Table 2. Main parameters of interference calculation model for tilt-wing aircraft
参数 数值 机翼翼型 NACA63018 前机翼面积/m2 8 机翼半展长/m 5 机翼安装角/（°） 3 机翼梢根比 0.7 襟翼展长/m 2.49 副翼展长/m 2.49 旋翼半径/m 0.9 旋翼实度 0.16 旋翼总拉力系数 0.0372 旋翼与机翼前缘平均距离/m 0.87
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