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首页> 外文期刊>Journal of guidance, control, and dynamics >Cyclic Blade Pitch Control Without a Swash plate for Small Helicopters
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Cyclic Blade Pitch Control Without a Swash plate for Small Helicopters

机译：小型直升机的不带斜盘的循环叶片桨距控制

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摘要

This paper presents the design, dynamical model, and experimental investigation of an articulated rotor that affords cyclic pitch authority in small unmanned air vehicle rotorcraft without requiring either a mechanical swashplate or blade pitch actuators. An offset flap hinge coincident with a skew lag-pitch hinge is used to impose a positive lag-pitch coupling on one rotor blade and a complementary negative lag-pitch coupling on the other. The motor torque driving the propeller is electronically modulated to excite a lead-lag motion with controlled rotational phase and amplitude; the ensuing once-per-revolution variation in blade pitch obtains the conventional control response and flapping character of fully actuated cyclic systems. The governing nondimensional lag-tlap equations including a nonconstant speed hub are shown. The experimentally measured motor torque, the huh speed variation, the cyclic blade lag-pitch response, and the cyclic blade flapping response are compared with model predictions.
机译：本文介绍了一种铰接式旋翼的设计，动力学模型和实验研究，该旋翼式旋翼可在小型无人飞行器旋翼机中提供周期性的俯仰角权限，而无需机械斜盘或桨距调节器。与偏斜滞后节距铰链重合的偏置襟翼合页用于在一个转子叶片上施加正滞后节距联接，而在另一转子叶片上施加互补的负滞后节距联接。对驱动螺旋桨的电动机扭矩进行电子调制，以控制旋转相位和幅度来激发超前-滞后运动；随之而来的桨距每转一次变化便获得了常规控制响应和全驱动循环系统的拍动特性。示出了包括非恒定速度轮毂的支配的无量纲滞后-拍击方程。将实验测得的电动机扭矩，速度变化，周期性叶片滞后-变桨响应和周期性叶片拍打响应与模型预测进行比较。

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