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为了得到旋翼升力与旋翼直径、桨叶角以及主轴转速之间的关系,以指导折叠翼无人飞行机器人的结构设计,采用正交试验法设计试验工况,在Fluent流体计算软件中进行数值计算,对计算结果加以分析;采用奇异值分解的最小二乘拟合算法处理试验数据,得出旋翼升力与旋翼系统参数之间的拟合公式;将拟合公式计算出的变形量理论值与对应试验值进行比较,结果表明:在试验涉及的桨叶角α∈[8.3°,14.3°]、主轴转速n∈[2 000 r/m in,4 000 r/m in]、旋翼直径d∈[480 m m,640m m]的范围内,检测误差不超过1.5%。
In order to obtain the relationship between rotor lift and rotor diameter, blade angle and spindle speed to guide the structural design of unmanned aerial vehicle with folded wing, the experimental conditions were designed by orthogonal experimental method and the numerical calculation was carried out in Fluent fluid calculation software , The results of the analysis are analyzed. The least squares fitting algorithm based on the singular value decomposition is used to process the experimental data, and the fitting formula between the rotor lift and the rotor system parameters is obtained. The theoretical value of the deformation calculated by the fitting formula is compared with the corresponding The experimental results show that when the blade angle α ∈ [8.3 °, 14.3 °], the spindle speed n ∈ [2000 r / m in, 4000 r / m in] and the rotor diameter d ∈ [ 480 mm, 640 m m], the detection error does not exceed 1.5%.