The invention relates to a method for obtaining rotor induced velocity distribution during tilting of a tilt-rotor aircraft. The method comprises the following steps: step 1, expressing rotor induced velocity as a function of a rotor radial position and an azimuth angle by using a first-order Fourier series; 2, determining a rotor blade tension coefficient, a rolling moment coefficient and a pitching moment coefficient according to aircraft body parameters and a rotor blade tilting process motion state; step 3, determining a time-average inflow component; 4, determining a first-order longitudinal inflow component and a first-order transverse inflow component; 5, rotor induced velocity distribution in the tilting process is obtained; and 6, performing rotor kinetic analysis according to the obtained rotor induced velocity distribution result, and perfecting the rotor blade optimization design. According to the method, the calculation result of the rotor induced velocity distribution can be obtained in real time, and compared with the calculation period of the rotor induced velocity distribution obtained through simulation calculation in the prior art, the speed is greatly increased.
本发明涉及一种获得倾转旋翼飞行器倾转时旋翼诱导速度分布的方法,包括如下步骤:步骤一、利用一阶傅立叶级数将旋翼诱导速度表达为旋翼径向位置和方位角的函数;步骤二、根据飞行器机体参数和旋翼桨叶倾转过程运动状态确定旋翼桨叶拉力系数、滚转力矩系数和俯仰力矩系数;步骤三、确定时均入流分量;步骤四、确定一阶纵向入流分量和一阶横向入流分量;步骤五、获得倾转过程旋翼诱导速度分布;步骤六、根据获得的旋翼诱导速度分布结果进行旋翼动力学分析并完善旋翼桨叶优化设计。本发明方法可即时获得旋翼诱导速度分布的计算结果,这和现有技术中利用仿真计算获得旋翼诱导速度分布的计算周期相比,速度大大加快。
Method for obtaining rotor induced velocity distribution during tilting of tilt-rotor aircraft
一种获得倾转旋翼飞行器倾转时旋翼诱导速度分布的方法
2024-01-16
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge / 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 / G06F ELECTRIC DIGITAL DATA PROCESSING , Elektrische digitale Datenverarbeitung |
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