Numerical Simulation of Tilting Wing and Rotor UAV During Transition Flight

doi:10.3969/j.issn.1009-086x.2024.03.002

Abstract

Abstract:

Compared with traditional configuration tiltrotor aircraft， tilting wing and rotor UAV can significantly reduce the aerodynamic interference of rotor wake on wings in hover， and increase flight efficiency. Regarding the continuous tilting transition process of the UAV with complex unsteady aerodynamic characteristics， the delayed detached eddy simulation （DDES） method， improved from the classical detached eddy simulation （DES） method， is used to simulate aerodynamic interference. During the tilting transition process， the aircraft's forward flight speed， rotor pitch angle， fuselage and fixed wing angle of attack， and nacelle inclination angle all dynamically change over time. By comparing with the traditional configuration， the aerodynamic performance changes and flow field mechanisms during the tilting transition process are analyzed. The simulation calculation results show that the UAV in the initial state of tilting is less affected by the rotor downwash. During the tilting process before the 30° nacelle inclination angle， due to the increased resistance of the tilting wing segment， the required thrust of the rotor are increased. The separation vortices generate during the tilting process of the tilting wing section collide with the downwash wake of the rotor， resulting in a larger wake interference area at the wing tip position and a downwash effect on the inner fixed wing tip， reducing the overall lift of the aircraft.

Key words: tilting wing, unmanned aerial vehicle（UAV）, the delayed detached eddy simulation, transition flight, aerodynamic interference, unsteady aerodynamic characteristics

摘要：

倾转机翼旋翼无人机相较于传统构型倾转旋翼机能够显著改善悬停状态旋翼尾迹对机翼的气动干扰影响，提高飞行效率。针对该构型无人机具有复杂非定常气动特性的连续倾转过渡过程，采用由经典的分离涡模拟方法（DES）改进得到的延迟分离涡模拟方法（DDES）对其进行流场气动干扰计算，倾转过渡过程中无人机前飞速度、旋翼桨距角、机身与固定翼迎角以及短舱倾转角都随时间动态变化。通过与无倾转机翼传统构型对比，分析了倾转过渡过程气动性能变化以及流场机理。仿真计算结果表明，倾转初始状态无人机受到旋翼下洗流影响较小，在30°短舱倾转角以前的倾转过程，由于倾转机翼段阻力增大，导致旋翼需用拉力增大。倾转机翼段在倾转过程中产生的分离涡与旋翼下洗流尾迹产生碰撞干扰，导致在机翼翼梢位置产生更大的尾迹干扰区域，并且对内侧固定翼翼梢产生下洗效果，降低了整机升力。

关键词: 倾转机翼, 无人机, 延迟分离涡模拟, 倾转过渡, 气动干扰, 非定常气动特性

CLC Number:

V211.52

Zonghui WANG, Yunjun YANG, Hongrui ZHAO, Jiaxiang ZHAO. Numerical Simulation of Tilting Wing and Rotor UAV During Transition Flight[J]. Modern Defense Technology, 2024, 52(3): 9-19.

王宗辉, 杨云军, 赵弘睿, 赵佳祥. 倾转机翼旋翼无人机倾转过渡状态数值模拟[J]. 现代防御技术, 2024, 52(3): 9-19.

Figures/Tables 16

Fig. 1 Schematic diagram of Georgia rotor/fuselage experimental model

Fig. 2 Grid diagram of rotor/fuselage interference

Fig. 3 Average pressure coefficient distribution

Fig. 4 Q-criterion isosurface of instantaneous flow field

Fig. 5 Geometric shape of tiltrotor

Table 1 Comparison of flight performance calculation results

飞行状态	悬停状态		巡航状态
飞行状态	拉力/N	扭矩/ （ $N ⋅ m$ ）	拉力/ N	扭矩/ （ $N ⋅ m$ ）
文献［32］RANS	2 413	359	233	169
本文RANS	2 487	373	249	180
本文DDES	2 502	375	253	184

Table 1 Comparison of flight performance calculation results

飞行状态	悬停状态		巡航状态
飞行状态	拉力/N	扭矩/ （ $N ⋅ m$ ）	拉力/ N	扭矩/ （ $N ⋅ m$ ）
文献［32］RANS	2 413	359	233	169
本文RANS	2 487	373	249	180
本文DDES	2 502	375	253	184

Fig. 6 Q-criterion isosurface of tiltrotor

Table 2 Geometric parameters of tilt wing and rotor UAV

参数	数值
短舱倾转角/（°）	0~90
旋翼旋转半径/m	1.6
旋转速度/（r·min^-1）	1 000
机翼参考弦长/m	0.726
机翼参考面积/m²	2.5
机翼安装角/（°）	0
倾转机翼占比总机翼长度	1/3

Fig. 7 Tilting transition attitude planning

Fig. 8 Grid diagram of tilting wing and rotor UAV

Fig. 9 Curve of lift and drag between the fuselage and wing

Fig. 10 Curve of changes for rotor thrust

Fig. 11 Curve of the component of rotor thrust in the forward flight direction and aircraft drag

Fig. 12 Distribution of wake vortices in the initial state

Fig. 13 Distribution of wake vortices in the transition process

Fig. 14 Surface pressure distribution profile

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