直升机旋翼锥体与动平衡主动调节技术

针对直升机桨叶质量、气动条件等不平衡引起的旋翼低频振动过大的问题,提出一种以旋翼锥体为约束、仅通过调整桨叶变距拉杆的主动减振技术.该技术在建立的桨叶挥舞摆振扭转耦合的动力学模型基础上,使用最小二乘辨识方法估计振动频域分量和变距拉杆位移之间的线性模型,从而构造并求解以旋翼锥体为约束条件、低频振动分量为控制目标的二次型性能指标函数,同时将该算法用Simulink模块实现,进行实时化仿真计算,并验证控制结果的有效性.结果表明：该算法约束旋翼锥体的同时能够降低旋翼80%以上的低频振动,而且对桨毂中心升力、扭矩等的影响在0.3%以内,并未对直升机其他动力响应产生不良影响,结合Simulink模型的实时化仿真为直升机锥体和动平衡调整提供了一种工程应用思路.

Active adjustment technology of helicopter rotor track and dynamic balance

Aiming at the problem of excessive low-frequency vibration of the rotor caused by the unbalance of the helicopter blade mass and aerodynamic, an active technology of vibration reduction that takes the rotor track as the constraint and only adjusts the blade pitch rods is proposed. This technology uses the least squares identification method to estimate the linear model between the vibration frequency domain component and the displacement of the pitch rod on the basis of the established blade flap-lag-torsion coupling dynamic model, thereby constructing and solving the quadratic performance index function which the rotor track is the constraint and the low-frequency vibration component is control objective. At the same time, the algorithm is implemented with Simulink module, real-time simulation calculation is performed, and the effectiveness of the control result is verified. The results show that the algorithm proposed can reduce the low-frequency vibration of the rotor by more than 80% while constraining the rotor track, and the influence on the lift and torque of the hub center is within 0.3%, and it has no adverse effect on the other dynamic response of the helicopter. Combined with Simulink, the real-time simulation of the model provides an engineering application idea for the adjustment of the helicopter track and dynamic balance.