A method for evaluating the wind disturbance rejection capability of a hybrid UAV in the quadrotor mode

IF 1.5 4区工程技术 Q2 ENGINEERING, AEROSPACE

International Journal of Micro Air Vehicles Pub Date : 2019-08-01 DOI:10.1177/1756829319869647

Hang Zhang, Bifeng Song, Haifeng Wang, J. Xuan

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引用次数: 15

Abstract

The wind disturbance rejection capability of a quadrotor fixed-wing hybrid unmanned aerial vehicle (QFHUAV) in the quadrotor mode is an important factor restricting its large-scale applications. In this paper, based on static equilibrium analysis of the quadrotor mode of a QFHUAV with a wind disturbance, a method for analyzing and evaluating the wind disturbance rejection capability of the QFHUAV in the quadrotor mode is presented. The six degrees-of-freedom (6-DOF) static equilibrium equations of the QFHUAV are established in headwind and crosswind situations. The maximum wind velocity that satisfies the equilibrium equations under the constraints of the maximum thrust and torque of the quadrotor propulsion system is used to determine the wind disturbance rejection capability of the QFHUAV in the quadrotor mode. A QFHUAV with a twin-boom is used as an example to analyze and evaluate its wind disturbance rejection capability in the quadrotor mode. The configuration parameters, quadrotor propulsion system parameters, and aerodynamic parameters affecting the wind disturbance rejection capability of the QFHUAV in the quadrotor mode are presented, discussed, and explained. The yawing moment from the wind disturbance is the main factor threatening the safe flight of the QFHUAV in the quadrotor mode. The rotor disk angle, the maximum thrust of the quadrotor propulsion system, and the moment arms of the components of the quadrotor propulsion system thrust are the main factors affecting the wind disturbance rejection capability of the QFHUAV in the quadrotor mode. Increasing these parameter values is an effective approach to improve the wind disturbance rejection capability of the QFHUAV in the quadrotor mode. From the perspective of wind disturbance rejection capability, tailless and X-type layouts are better choices for QFHUAVs. The correctness of results obtained by the proposed method is verified by two flight test schemes.

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一种评估混合动力无人机在四旋翼模式下抗风扰能力的方法

四旋翼固定翼混合动力无人机在四旋翼模式下的抗风扰动能力是制约其大规模应用的重要因素。本文在对四旋翼飞行器在风扰动作用下的静平衡分析的基础上，提出了一种四旋翼飞行器抗风扰动能力的分析与评价方法。建立了逆风和侧风条件下qfwav的六自由度静力平衡方程。在四旋翼推进系统最大推力和扭矩约束下满足平衡方程的最大风速，用于确定四旋翼模式下QFHUAV的抗风扰动能力。以双臂qfwav为例，对其四旋翼抗风能力进行了分析和评价。对四旋翼模式下影响QFHUAV抗风能力的构型参数、四旋翼推进系统参数和气动参数进行了分析、讨论和解释。风扰动引起的偏航力矩是威胁四旋翼无人机安全飞行的主要因素。旋翼盘角、四旋翼推进系统的最大推力、四旋翼推进系统各部件的力臂推力是影响四旋翼模式下QFHUAV抗风扰动能力的主要因素。提高这些参数值是提高四旋翼模式下QFHUAV抗风扰动能力的有效途径。从抗风扰动能力来看，无尾布局和x型布局是qfhuav较好的选择。通过两种飞行试验方案验证了所提方法的正确性。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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来源期刊

International Journal of Micro Air Vehicles ENGINEERING, AEROSPACE-

CiteScore

3.00

自引率

7.10%

发文量

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.