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为建立实时性和精度高的直升机旋翼升力模型,基于动量-叶素法,以理想扭转型桨叶为例,给出了旋翼诱导速度的计算模型.在考虑桨叶挥舞运动的前提下,利用八占位法和给出的诱导速度模型,以桨尖安装角为人工输入,提出了有初值的关于旋翼升力、机身速度和诱导速度的迭代计算流程.实验结果表明:将实际飞行数据和利用该计算流程生成的仿真曲线相对比,二者机身的滚转特征曲线具有相同的走势,旋翼系数曲线又具有较高的拟合度,并且各动力学仿真参数能够随着人工输入迅速合理地作出响应,从而分别验证了该旋翼升力模型的可靠性、精确性和实时性.
In order to establish a helicopter rotor lift model with real-time and high accuracy, a rotor-induced speed calculation model is given based on the momentum-vane method and the ideal torsion type blade.Under the premise of blade waving movement, Bit method and the induced velocity model are given, and the tip angle is used as the manual input. An initial iterative calculation flow about rotor lift, fuselage velocity and induced velocity is proposed. The experimental results show that the actual flight data and utilization The simulation curves generated by this calculation process have the same trend as the roll characteristic curves of the two fuselages and the curve coefficients of the rotor have a higher fitting degree, and the dynamic simulation parameters can be quickly and reasonably In response, the reliability, accuracy and real-time performance of the rotor lift model were verified.