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Initial conceptual design and wing aerodynamic analysis of a solar power-based UAV

机译：基于太阳能的无人机的初步概念设计和机翼空气动力学分析

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摘要

King Abdul Aziz University of Saudi Arabia (KAU) and Tokai University in Japan have collaborated to design and manufacture a solar powered unmanned air vehicle (UAV), Sun Falcon, which has capability of continuous one day flight with intended design extension towards night flight. The project is a student-driven endeavour involving some 30 students. Both universities are equally involved in the actual design studies of the performance characteristics, aerodynamic design, propulsion and structural analysis. Tokai University is in charge of the actual on-site supervision and examination of on-going manufacturing processes and ultimate fabrication of the prototype model. The conceptual design of the Sun Falcon was meticulously worked out in consideration of the operational mission, which included such flight characteristics as the cruising velocity, flight altitude, payload, flight time, rate of climb, power requirements and so on. The weather condition patterns in Saudi Arabia, which remained fairly supportive of the solar cell performance, were also deemed crucial in the design process. However, the design of a solar plane had other challenges in terms of power unit accommodation and payload consideration in comparison to other conventional UAVs. In this paper, an outline of the design features of the Sun Falcon is presented and other notable design features particular to solar UAVs are discussed. It was learnt in this exercise that the selection of the base aerofoil is perhaps one of the most important design items, as the Reynolds number for such UAVs understandably drops notably lower than conventional aeroplanes and such features as the camber curvature and wing area must cater for the installation of solar panels whose size, strength and quantity must respect local weather conditions. For the Sun Falcon, the actual design process examined two candidate aerofoils FX74-CL5-140 (FX74) and SD7037-092-88(SD7037) both of which were abundantly suitable for furnishing the required aerodynamic characteristics. SD7037 was ultimately chosen as it provided the best geometry and camber line in terms of accommodation and placement of the solar panels. Further scrutiny demonstrated that this latter aerofoil provided better take-off performance and superior L/D behaviour under cruise conditions. In order to check out the aerodynamic performance in general and overall stability and control characteristics, a preflight test under battery power (a 2,500 mAh li-po 4-cell 14·8v) was achieved on 4 June 2013. Other solar powered based tests are currently under way at present.
机译：沙特阿拉伯阿卜杜勒·阿齐兹国王大学（KAU）和日本东海大学合作设计制造了太阳能无人飞行器（UAV）Sun Falcon，它具有连续一天的飞行能力，并打算将设计扩展到夜间飞行。该项目是一项由学生主导的工作，涉及约30名学生。两所大学均平等参与性能特征，空气动力学设计，推进和结构分析的实际设计研究。东海大学负责正在进行的制造过程的实际现场监督和检查，以及原型模型的最终制造。太阳猎鹰的概念设计是根据作战任务精心设计的，其中包括飞行特性，例如巡航速度，飞行高度，有效载荷，飞行时间，爬升率，功率要求等。在设计过程中，沙特阿拉伯的天气状况模式（仍然相当支持太阳能电池的性能）也被认为是至关重要的。然而，与其他常规无人机相比，太阳能飞机的设计在动力单元容纳和有效载荷考虑方面还面临其他挑战。在本文中，概述了“太阳猎鹰”的设计特征，并讨论了太阳能无人机所特有的其他显着设计特征。在这次演习中得知，机翼基础件的选择也许是最重要的设计项目之一，因为这种无人机的雷诺数明显低于传统飞机，而且弯度和机翼面积等特征必须满足这一要求安装太阳能电池板，其尺寸，强度和数量必须遵守当地的天气条件。对于Sun Falcon，实际设计过程检查了两种候选机翼FX74-CL5-140（FX74）和SD7037-092-88（SD7037），它们都非常适合提供所需的空气动力学特性。最终选择SD7037是因为它在太阳能电池板的容纳和放置方面提供了最佳的几何形状和弧度线。进一步的研究表明，后一种翼型在巡航条件下具有更好的起飞性能和出色的L / D性能。为了检查空气动力学性能的总体和整体稳定性以及控制特性，2013年6月4日在电池电源（2,500 mAh锂电池4节电池14·8v）下进行了飞行前测试。其他基于太阳能的测试包括目前正在进行中。

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  • 来源
    《The Aeronautical Journal》 |2014年第1203期|540-554|共15页
  • 作者

    W. Harasani; M. Khalid; N. Arai; K.Fukuda; K. Hiraoka;

  • 作者单位

    King Abdul Aziz University Jeddah Saudi Arabia;

    King Abdul Aziz University Jeddah Saudi Arabia;

    Tokai University Hiratsuka-city Japan;

    Tokai University Hiratsuka-city Japan;

    Tokai University Hiratsuka-city Japan;

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