Aerodynamic and structural design of a solar-powered micro unmanned air vehicle

2000 ◽  
Vol 214 (2) ◽  
pp. 97-106 ◽  
Author(s):  
C Wilson ◽  
J Nutbean ◽  
I Bond
Keyword(s):  
Structural Design ◽  
Solar Power ◽  
Size Range ◽  
Small Scale ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Solar Powered ◽  
Aircraft System ◽  
Technological Improvements ◽  
Aircraft Configurations

The field of micro unmanned aerial vehicles ((μUAVs) has advanced rapidly in recent years. This paper studies the design and construction of a small solar-powered aircraft near the size range of current (μUAVs. A number of aspects of their design were analysed, including structural, aerodynamic and propulsion system considerations. The effect of small-scale, low Reynolds number aerodynamics was investigated, and the performance of a range of candidate aerofoils was compared. The integration of a solar power source into the aircraft system was considered a key design issue. Consequently, a number of aircraft configurations were examined, with the intention of optimizing the application of solar power in a miniature aircraft. Investigation of improved system components suggests that a practical solar-powered aircraft in the size range below 500 mm maximum linear dimension should be viable given modest technological improvements.

Design, analysis and experimental validation of a morphing UAV wing

2011 ◽  
Vol 115 (1174) ◽  
pp. 761-765 ◽  
Author(s):  
M. Bolinches ◽  
A. J. Keane ◽  
A. I. J. Forrester ◽  
J. P. Scanlan ◽  
K. Takeda
Keyword(s):  
Structural Design ◽  
Experimental Validation ◽  
3D Printer ◽  
Hot Wire ◽  
Polystyrene Foam ◽  
Element Analysis ◽  
Roll Control ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
The University

Abstract The design of wings with morphing capabilities is known to give aerodynamic benefits. These aero-dynamic benefits come from both the use of hinge-less surfaces and the greater adaptability to flight conditions. This paper describes the structural design of a twisting wing to be used for an unmanned air vehicle (UAV) and presents finite element analysis and experiment results. This is part of a research project carried out at the University of Southampton in which one of the goals is to compare different novel wing designs and technologies to determine which one of them gives the best performance. The twisting capability provides roll control without hinged surfaces hence providing aerodynamic improvement. The wing is manufactured using polystyrene foam and is cut out of block of this material using a hot wire machine. In order to link this foam structure to a main spar, ABS plastic inserts were manufactured using a 3D printer. The mechanisms used to actuate the wing are also made from this material. A full scale UAV wing has been manufactured and tested in order to compare with FEA results.

Preliminary reliability design of a solar-powered high-altitude very long endurance unmanned air vehicle

2002 ◽  
Vol 216 (4) ◽  
pp. 189-196 ◽  
Author(s):  
G Frulla
Keyword(s):  
Traffic Monitoring ◽  
Cell Array ◽  
Reliability Design ◽  
Unmanned Air Vehicle ◽  
Simulation Based ◽  
Air Vehicle ◽  
Solar Powered ◽  
Propulsion Unit ◽  
Simple Systems ◽  
Long Endurance

Within the research project HELINET (network of stratospheric platforms for traffic monitoring, environmental surveillance and broadband services), a preliminary reliability design is performed in conjunction with the platform design. The aim of the discussion consists in determining the configuration of the propulsion system and in the choice of the number of propulsion units (a propulsion unit consists of one propeller and one or more motors). The reliability and the weight of different very simple systems are evaluated and compared with one another in order to indicate the best one. The analysis of the fleet reliability and a study of its standby platforms is also taken into consideration. The analysis of the reliability of the solar cell array is also an interesting issue. A parametric analysis based on well-known formulae is used. Some results are verified by means of a numerical simulation based on the Monte Carlo methodology. Some important design indications could be obtained from this effort.

Design, Modelling and Simulation of Maritime UAV-VTOL Flight Dynamics

2012 ◽  
Vol 152-154 ◽  
pp. 1533-1538
Author(s):  
Jun Cao ◽  
Amir M. Anvar
Keyword(s):  
Structural Design ◽  
Water Surface ◽  
Unmanned Aircraft ◽  
The Other ◽  
Underwater Robot ◽  
Unmanned Air Vehicle ◽  
Vtol Uav ◽  
Air Vehicle ◽  
Remotely Piloted Aircraft ◽  
Aerial Vehicle

An Unmanned Aerial Vehicle (UAV) is referred to as a remotely piloted aircraft or an unmanned aircraft which can be navigated with human operator in the loop. This paper discusses the design of a UAV with Vertical Take-Off and Landing (VTOL) capability for Maritime applications. The design provides a means for surveillance and communication in Maritime applications. The VTOL-UAV utilises a five-rotor propulsion system that can be launched from confined platforms such as ship-decks. The intended applications of this M-UAV drove the development of an innovative landing system which in the case of emergencies can allow the M-UAV’s soft and potential landing on the water surface. The other functionalities of this UAV are its capabilities to deploy communication Micro-sonobuoys which allows for communication with underwater Robot(s) via Operator in the loop. In this paper we also discuss the process of structural design modelling and evaluation of the development of the Maritime Unmanned Air Vehicle.

Design of a Solar Powered, Unmanned, Low Altitude, High Endurance Airship

2015 ◽  
Vol 798 ◽  
pp. 556-564 ◽  
Author(s):  
Onur Sinan Sonmez ◽  
H. Nafiz Alemdaroglu
Keyword(s):  
Design Parameters ◽  
Design Criteria ◽  
Detailed Design ◽  
General Design ◽  
Design Specifications ◽  
Unmanned Air Vehicle ◽  
Air Vehicle ◽  
Low Altitude ◽  
Solar Powered ◽  
Long Endurance

This article presents the design of a low altitude long endurance solar powered unmanned airship. In the first part of the article, a brief introduction about the airships, their potential areas of usage, the advantages of using an unmanned air vehicle, and a comparison between unmanned counterparts will be given. In the second part, the design criteria and the general design specifications will be outlined briefly. During the design, emphasis is given on the general design parameters of the Lighter Than Air (LTA) vehicles. Lastly, the detailed design results, in order to reach the projected design parameters, have been presented.

Clogging in Irrigation Systems Reusing Pond Effluents and its Prevention

1987 ◽  
Vol 19 (12) ◽  
pp. 323-328 ◽  
Author(s):  
A. Adin
Keyword(s):  
Size Range ◽  
Small Scale ◽  
Main Obstacle ◽  
Reservoir Systems ◽  
Deep Reservoir ◽  
Particulate Removal ◽  
Oxidation Ponds ◽  
Surface Filtration ◽  
Granular Filtration ◽  
Low Rate

The clogging of emitters, orifices or laterals has turned out to be the main obstacle for further use of low rate applicators in wastewater irrigation. Granular filtration and screen filtration were studied and compared for particulate removal using small-scale pilot experiments. The removal ratio of particles larger than 10 µm in direct granular filtration was relatively large while smaller particles showed little removal. Particles in the 10-60µm size range were removed by 40–50 percent in depth and by 80 percent when surface filtration prevailed. Screen filters removed only 1–2 percent of the material but this was sufficient to cause their clogging. A release of particles from the screen into the effluent was observed, resulting in greater number of larger particles and thus greater clogging potential down the irrigation line. Deep-bed granular coarse media filters may serve for the control of particle size in effluents of oxidation ponds - deep reservoir systems while the conventional strainers are less recommended for this purpose.

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