Dynamics analysis, control and flight test of all-wing tail-sitter configuration solar powered UAV

IF 5.8 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology Pub Date : 2025-09-17 DOI:10.1016/j.ast.2025.110945

Xin Zhao , Zhou Zhou , Jiayue Hu , Kelei Wang , Baiyang Li

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Abstract

This paper proposes a novel all-wing tail-sitter Vertical Take-off/Landing (VTOL) solar-powered Unmanned Aerial Vehicle (UAV) configuration. It adopts thrust differential control instead of traditional aerodynamic control surfaces to maximize the solar panel layout area and the photovoltaic energy-harvesting power. Compared to conventional electric VTOL (eVTOL) aircraft, this design achieves over sixfold improvement in endurance. To address insufficient control effectiveness caused by the large wingspan and low wing loading, a variable thrust installation angle is designed. A dynamic model incorporating the propulsive-aerodynamic coupling effects between the propeller slipstream and the wing, along with the thrust installation configuration, is developed. Detailed stability and maneuverability analysis demonstrates that, the designed thrust installation angle effectively enhances roll control authority during VTOL phases and benefits longitudinal static stability in level flight, without significantly compromising dynamic stability. Aiming at the nonlinear propulsive-aerodynamic coupling and model errors, an INDI-based unified attitude control law is designed and evaluated through simulations and full-envelope flight tests, confirming the control effectiveness and configuration feasibility. Furthermore, the maximum endurance performance of the prototype is discussed based on the power data collected during flight and the numerical model of solar irradiance.

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全翼坐式太阳能无人机动力学分析、控制及飞行试验

提出了一种新型全翼尾翼式垂直起降（VTOL）太阳能无人机（UAV）结构。采用推力差动控制取代传统气动控制面，最大限度地提高太阳能板布局面积和光伏集能功率。与传统的电动垂直起降（eVTOL）飞机相比，这种设计在续航力上实现了六倍以上的改进。针对大翼展和低翼载导致的控制效果不足的问题，设计了可变推力安装角。建立了考虑螺旋桨滑流与机翼之间推进-气动耦合效应以及推力装置配置的动力学模型。详细的稳定性和机动性分析表明，所设计的推力安装角有效地提高了垂直起降阶段的滚转控制权威，有利于水平飞行时的纵向静稳定性，且动态稳定性不受明显影响。针对非线性推进气动耦合和模型误差，设计了基于indii的统一姿态控制律，并通过仿真和全包线飞行试验对其进行了评价，验证了控制的有效性和构型的可行性。在此基础上，结合飞行过程中采集的功率数据和太阳辐照度数值模型，讨论了原型机的最大续航性能。

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

Aerospace Science and Technology 工程技术-工程：宇航

CiteScore

10.30

自引率

28.60%

发文量

654

审稿时长

54 days

期刊介绍： Aerospace Science and Technology publishes articles of outstanding scientific quality. Each article is reviewed by two referees. The journal welcomes papers from a wide range of countries. This journal publishes original papers, review articles and short communications related to all fields of aerospace research, fundamental and applied, potential applications of which are clearly related to: • The design and the manufacture of aircraft, helicopters, missiles, launchers and satellites • The control of their environment • The study of various systems they are involved in, as supports or as targets. Authors are invited to submit papers on new advances in the following topics to aerospace applications: • Fluid dynamics • Energetics and propulsion • Materials and structures • Flight mechanics • Navigation, guidance and control • Acoustics • Optics • Electromagnetism and radar • Signal and image processing • Information processing • Data fusion • Decision aid • Human behaviour • Robotics and intelligent systems • Complex system engineering. Etc.