The invention provides a trailing edge flap type intelligent rotor wing and a flap hinge moment estimation method thereof, and the method comprises the steps: 1, obtaining a flap deflection angle phi flap in a driving mechanism and simulated aerodynamic force F of the flap in the driving mechanism through a bench test of the flap driving mechanism of the intelligent rotor wing; 2, according to the simulated aerodynamic force F of the flap and the force arm r from the spring load applying point to the flap rotating shaft, the hinge moment N of the flap in the bench test is calculated. 3, establishing a mapping relation between the flap hinge moment N and the flap deflection angle phi flap; 4, a rotation test of the intelligent rotor wing is carried out, and the flap deflection angle theta 0 in the flight state is obtained. And 5, substituting the flap deflection angle theta0 in the flight state into the mapping relation N = F (phi) to obtain the flap hinge moment load N = F (theta0) of the trailing edge flap type intelligent rotor in rotational motion.
本申请提供一种后缘襟翼型智能旋翼及其襟翼铰链力矩的预估方法,所述方法包括:步骤1:通过智能旋翼襟翼驱动机构台架试验,获得驱动机构中襟翼偏转角φ襟翼和襟翼的模拟气动力F气动力;步骤2:根据襟翼的模拟气动力F气动力和弹簧负载施加点到襟翼旋转轴的力臂r,计算台架试验中襟翼的铰链力矩N。步骤3:建立襟翼铰链力矩N与襟翼偏转角φ襟翼的映射关系;步骤4:开展智能旋翼的旋转试验,获得飞行状态下的襟翼偏转角θ0。步骤5:将飞行状态下的襟翼偏转角θ0代入映射关系N=F(Φ),获得旋转运动中后缘襟翼型智能旋翼的襟翼铰链力矩载荷N=F(θ0)。
Tailing edge flap type intelligent rotor wing and method for estimating flap hinge moment of trailing edge flap type intelligent rotor wing
一种后缘襟翼型智能旋翼及其襟翼铰链力矩的预估方法
03.01.2025
Patent
Elektronische Ressource
Chinesisch