The invention discloses a multi-rotor aircraft rotor intersection inclination angle optimization method, which comprises a rotor intersection inclination configuration method and a specific analysis and optimization method of a rotor intersection inclination angle. According to the method, the influence of the rotor wing cross inclination angle on each channel accelerator of the aircraft and the influence of the rotor wing inclination installation error on the yaw control accelerator can be comprehensively considered. According to the rotor wing cross inclination angle obtained through optimization, the control effect of yaw motion of the multi-rotor aircraft can be improved, the yaw control accelerator amount can be reduced, coupling between the multi-rotor aircraft and attitude and lift force control channels can be reduced as much as possible, and the requirement for installation precision of a rotor wing power system is further lowered.
本发明公开了一种多旋翼飞行器的旋翼交叉倾斜角优化方法,包括旋翼交叉倾斜配置方法,以及旋翼交叉倾斜角的具体分析和优化方法。本发明方法可以综合考虑旋翼交叉倾斜角对飞行器各个通道油门的影响,以及旋翼倾斜安装误差对偏航控制油门的影响。通过本发明优化得到的旋翼交叉倾斜角,既可以提高多旋翼飞行器偏航运动的操纵功效,降低偏航控制油门量,又能尽量减小其与姿态、升力控制通道的耦合,并进一步降低旋翼动力系统安装精度的要求。
Rotor wing cross inclination angle optimization method of multi-rotor aircraft
一种多旋翼飞行器的旋翼交叉倾斜角优化方法
2022-03-22
Patent
Elektronische Ressource
Chinesisch
IPC: | G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen |
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