Unsteady aerodynamic interference of tilt-quadrotor due to multi-vortex effect
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摘要:
针对倾转四旋翼机直升机模式和固定翼模式存在的复杂气动干扰现象，基于CFD方法建立了一套适用于倾转四旋翼机全机干扰流场模拟的数值方法，系统模拟了旋翼多涡系与机翼、机身之间的气动干扰，揭示了非定常气动特性的发生和演化机理。结果表明：在直升机模式下，前旋翼产生的桨根涡会作用在前机翼上表面，并在机翼下方卷起二次涡。后旋翼产生的桨根涡会受到前旋翼桨尖涡吸引，发生明显的左移现象并作用在后机翼前缘处；在固定翼模式下，前旋翼拖出的桨尖涡会快速向后移动，与后旋翼发生的气动干扰现象较少，前/后旋翼对机身压力分布影响较小，机身整体表现出典型固定翼机身压力特性。
Abstract:Considering the complex aerodynamic interference phenomena in the helicopter and fixed-wing modes of the tilt-quadrotor, a set of numerical methods suitable for simulation of the interference flow field of the tilt-quadrotor were established based on the CFD method. The aerodynamic interference between the rotor multi-vortex system and the wing and fuselage was systematically simulated, and the occurrence and evolution mechanisms of unsteady aerodynamic characteristics were revealed. The results showed that in the helicopter mode, the blade root vortex generated by the front rotor could act on the upper surface of the front wing and roll up the secondary vortex below the wing. The blade root vortex generated by the rear rotor could be attracted by the tip vortex of the front rotor, and the obvious left shift phenomenon may occur and act on the leading edge of the rear wing. In the fixed-wing mode, the tip vortex dragged out by the front rotor could move backward rapidly, and the aerodynamic interference with the rear rotor was less. The front/rear rotor had less influence on the fuselage pressure distribution, and the fuselage as a whole showed typical fixed-wing fuselage pressure characteristics.
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图 2 直升机模式倾转四旋翼机计算网格示意图
Figure 2. Computational grid of tilt-quadrotor in helicopter mode
图 3 倾转四旋翼机固定翼模式计算网格示意图
Figure 3. Computational grid of tilt-quadrotor in fixed-wing mode
图 4 XV-15不同飞行状态旋翼气动特性计算值与试验值对比
Figure 4. Comparison of calculated and experimental values of rotor aerodynamic characteristics of XV-15 under different flight conditions
图 5 倾转四旋翼机直升机模式计算模型示意图
Figure 5. Calculation model diagram of tilt-quadrotor in helicopter mode
图 6 直升机模式倾转四旋翼机涡流场图
Figure 6. Eddy current field diagram of tilt-quadrotor in helicopter mode
图 7 直升机模式倾转四旋翼机身不同站位涡量图
Figure 7. Vorticity diagram of tilt-quadrotor fuselage at different stations in helicopter mode
图 8 直升机模式倾转四旋翼机身压力系数云图
Figure 8. Pressure coefficient cloud diagram of tilt-quadrotor fuselage in helicopter mode
图 9 直升机模式倾转四旋翼机不同机翼站位处涡量图
Figure 9. Vorticity diagram of tilt-quadrotor at differen wing stations in helicopter mode
图 10 直升机模式前机翼压力系数及云图
Figure 10. Front wing pressure coefficient and cloud diagram in helicopter mode
图 11 直升机模式后机翼压力系数及云图
Figure 11. Back wing pressure coefficient and cloud diagram in helicopter mode
图 12 直升机模式旋翼-机翼拉力系数变化图
Figure 12. Rotor-wing tension coefficient variation diagram in helicopter mode
图 13 直升机模式前/后旋翼不同方位角前旋翼表面压力系数
Figure 13. Front rotor surface pressure coefficients of front/rear rotor at different azimuth angles in helicopter mode
图 14 直升机模式前/后旋翼中心平面${v_Z}$云图
Figure 14. ${v_Z}$ cloud diagram of front/rear rotor center plane in helicopter mode
图 15 前旋翼-后旋翼拉力系数随旋翼周期变化图
Figure 15. Front-rear rotor thrust coefficient varies with the rotor period
图 16 倾转四旋翼机固定翼模式涡流场
Figure 16. Eddy current field of tilt-quadrotor in fixed-wing mode
图 17 固定翼模式倾转四旋翼机不同机身站位涡量图
Figure 17. Vortex diagram of tilt-quadrotor at different fuselage stations in fixed-wing mode
图 18 固定翼模式倾转四旋翼机机身压力系数云图
Figure 18. Pressure coefficient cloud diagram of tilt-quadrotor fuselage in fixed-wing mode
图 19 倾转四旋翼机不同机翼站位压力分布及流线图
Figure 19. Pressure coefficient distribution and streamline diagram of tilt-quadrotor at different wing stations
图 20 固定翼模式倾转四旋翼不同机翼站位涡流图
Figure 20. Eddy current diagram of tilt-quadrotor at different wing stations in fixed-wing mode
图 21 固定翼模式前/后机翼不同截面压力系数图
Figure 21. Pressure coefficients of front/rear wings on different sections in fixed-wing mode
图 22 固定翼模式前/后机翼压力系数云图
Figure 22. Pressure coefficient cloud diagram of front/rear wing in fixed-wing mode
图 23 固定翼模式旋翼/机翼拉力系数周期变化图
Figure 23. Periodic variation diagram of rotor/wing tension coefficient in fixed-wing mode
图 24 固定翼模式前/后旋翼不同方位角旋翼压力系数
Figure 24. Rotor pressure coefficients of front/rear rotor with different azimuth angles in fixed-wing mode
图 25 固定翼模式过前/后旋翼中心平面诱导速度云图
Figure 25. Induced velocity cloud diagram of the front/rear rotor center plane in the fixed-wing mode
图 26 固定翼模式前/后旋翼拉力系数随旋翼周期变化图
Figure 26. Variation diagram of the front/rear rotor tension coefficient with the rotor period in the fixed-wing mode
表 1 倾转四旋翼机身主要参数
Table 1. Main parameters of tilt-quadrotor fuselage
参数 数值 机长/m 4.7 机高/m 1.3 前翼展/m 3.0 后翼展/m 3.8 前机翼安装角/（°） 3.3 后机翼安装角/（°） 3.0 前旋翼与前机翼相对位置/m 0.6 后旋翼与后机翼相对位置/m 0.6 机翼后掠角/（°） 0 机翼上反角/（°） 0 最大起飞质量/kg 700 
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表 2 倾转四旋翼机旋翼主要参数
Table 2. Main parameters of tilt-quadrotor rotor
参数 数值及说明 旋翼翼型 XV-15旋翼翼型 旋翼半径/m 1.0 旋翼根切/% 10 桨尖速度/（m/s） 210 桨叶片数（旋翼）/片 3 旋翼纵向间距/m 1.9 旋翼垂向间距/m 0.25 旋翼横向间距/m 0.4
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表 3 直升机模式前后机翼对旋翼气动特性影响
Table 3. Influence of front and rear wings on rotor aerodynamic characteristics in helicopter mode
计算状态 前旋翼
拉力系数前机翼
升力/N后旋翼
拉力系数后机翼
升力/N全机干扰 0.0131 −308 0.0129 −465 旋翼无机身 0.0127 0 0.0126 0
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表 4 直升机模式前/后旋翼干扰对各自气动力影响
Table 4. Influence of front/rear rotor interference on their respective aerodynamic forces in helicopter mode
计算状态 前旋翼拉力系数 后旋翼拉力系数 前/后旋翼带机身 0.0131 0.0129 孤立前/后旋翼 0.0132 0.0134
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表 5 固定翼模式旋翼对前后机翼气动特性影响
Table 5. Influence of fixed-wing mode rotor on the aerodynamic characteristics of front and rear wings
计算状态 升力系数 阻力系数 前机翼 后机翼 前机翼 后机翼 带旋翼机身 0.3414 0.2471 0.0256 0.0353 无旋翼机身 0.3111 0.2282 0.0266 0.0298
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表 6 固定翼模式旋翼对前后机翼气动特性影响
Table 6. Influence of fixed-wing mode rotor on the aerodynamic characteristics of front and rear wings
计算状态 前旋翼拉力系数 后旋翼拉力系数 前/后旋翼带机身 0.001 0.0015 后旋翼带机身 0 0.0016
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