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为提高旋翼型微型、小型飞行器桨叶的升力性能,建立了一套基于悬停状态下的单旋翼、共轴双旋翼桨叶扭转设计方法。该方法通过理论推导和程序计算得到单旋翼的桨叶扭转几何安装角,考虑桨尖涡对桨叶几何安装角的影响,对桨尖的扭转几何安装角进行了修正,实现悬停状态下单旋翼桨叶扭转设计;考虑到桨尖涡以及上下旋翼间的气动干扰,对共轴双旋翼上、下旋翼进行了悬停状态下几何安装角的扭转设计,并对所设计的单旋翼、共轴双旋翼进行模拟仿真测试,仿真结果表明悬停状态下该方法设计的扭转单旋翼、共轴双旋翼与非扭转旋翼相比升力分别提升8.83%、35.87%;同时对水平风阻、翼展、转速对桨叶升力的影响进行了仿真模拟。
In order to improve the lift performance of aero-rotor miniature and small aircraft propeller blades, a set of single-rotor and co-axial twin rotor blade torsion design method based on hovering condition is established. In this method, the torsional geometric installation angle of the blade is obtained by theoretical derivation and program calculation. The influence of the blade tip vortex on the geometric installation angle of the blade is considered, and the torsional geometric installation angle of the blade tip is corrected. Considering the tip vortex and the aerodynamic interference between the upper and lower rotors, the torsional design of the geometrical mounting angles of the upper and lower halves of the coaxial double-rotor blades in a hovering mode is carried out. The designed single-rotor The simulation results show that the designed single-rotor and single-rotor twin-rotor with hovering state are respectively 8.83% and 35.87% higher than the non-twisted rotor in the hovering state. Simultaneously the horizontal wind resistance, The effect of rotational speed on blade lift is simulated.