中尺度双旋翼直升机悬停飞行动力学模型辨识

IF 1.5 4区 工程技术 Q2 ENGINEERING, AEROSPACE
Carl Runco, Moble Benedict
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引用次数: 0

摘要

本文根据飞行试验数据,建立了一架33克双环直升机的线性时不变(LTI)动力学模型,对其飞行动力学进行了分析。双环直升机是一种新型微型飞行器,使用两个同向旋转摆线转子产生推力和同轴机头转子抵消反作用力并提供额外推力。在飞行试验中,对悬停状态进行摄动机动以激发不同模式,三维运动捕捉系统采集姿态和位置数据。利用这些数据,利用时域系统辨识技术提取悬停状态线性化的裸机体LTI模型。该模型表明,横摇和偏航模式与稳定的高频和低频模式是陀螺耦合的。对比摆线转子推力矢量和同轴机头转子差转矩两种不同的偏航控制方法,前者更有效。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Flight dynamics model identification of a meso-scale twin-cyclocopter in hover
In this paper the flight dynamics of a 33-gram twin-cyclocopter is analyzed via deriving a Linear Time Invariant (LTI) dynamics model from flight test data. The twin-cyclocopter is a novel micro air vehicle that uses two co-rotating cycloidal rotors to generate thrust and a coaxial nose rotor to counteract the reaction torque and provide additional thrust. During flight tests, perturbation maneuvers were performed about the hovering state to excite different modes and a 3D motion capture system collected attitude and position data. The data was used to extract a bare airframe LTI model linearized about the hovering state using time-domain system identification techniques. The model demonstrated that the roll and yaw modes are gyroscopically coupled with stable high-frequency and low-frequency modes. Comparing the two different yaw control methods: thrust vectoring of the cycloidal rotors and differential torque of the coaxial nose rotor, the former was more effective.
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来源期刊
CiteScore
3.00
自引率
7.10%
发文量
13
审稿时长
>12 weeks
期刊介绍: The role of the International Journal of Micro Air Vehicles is to provide the scientific and engineering community with a peer-reviewed open access journal dedicated to publishing high-quality technical articles summarizing both fundamental and applied research in the area of micro air vehicles.
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