Please use this identifier to cite or link to this item: https://hdl.handle.net/10356/60106
Full metadata record
DC FieldValueLanguage
dc.contributor.authorOh, Ying Qun
dc.date.accessioned2014-05-22T05:42:54Z
dc.date.available2014-05-22T05:42:54Z
dc.date.copyright2014en_US
dc.date.issued2014
dc.identifier.urihttp://hdl.handle.net/10356/60106
dc.description.abstractUnmanned Aerial Vehicles (UAVs) are aircrafts without a pilot on board and are employed in a variety of applications. The design of UAVs has been intensively researched over the past century and in the recent decades has evolved tremendously in terms of technology. The use of solar cells as a power source promises long endurance flights, while application of advanced materials such as carbon fibre dramatically reduces weight while maintaining structural integrity. The idea of a solar-powered UAV was proposed over 30 years ago and prototypes has already been tested and developed by both governmental and commercial agencies in US and UK. This collaborative project between NTU and DSO aims to build one of Singapore’s first such vehicles. The high altitude, long endurance (HALE) UAV will have an 18m wingspan, with solar panels acting as the upper wing skin. It will also be manufactured almost entirely out of carbon fibre. This report focuses on the structural design of the UAV specifically that of the wing assembly. It seeks to present innovative ideas to integrate avionics, propulsion and solar components with the wing structure. With the help of computer aided design and simulation software, dimensions and material usage of components were optimised for weight reduction and strength. Tests were also conducted on a 1-metre long spar specimen to verify theoretical calculations and determine their feasibility as the main load-bearing component. Structural joints between components, either permanent or removable, were also carefully thought out and modelled. Eventually, parts for a 3.2 metres test wing section was fabricated and assembled to demonstrate all structural features designed. In working towards building an airworthy prototype, further testing should be done on the test section. More load cases should also be examined, and material testing conducted, to ensure the UAV is versatile and structurally strong enough to survive unscathed under different flying manoeuvres and environmental conditions.en_US
dc.format.extent154 p.en_US
dc.language.isoenen_US
dc.rightsNanyang Technological University
dc.subjectDRNTU::Engineering::Aeronautical engineeringen_US
dc.titleRedesign, analysis, fabrication and testing of light weight wing for solar UAV : part 2en_US
dc.typeFinal Year Project (FYP)en_US
dc.contributor.supervisorLi Peifengen_US
dc.contributor.schoolSchool of Mechanical and Aerospace Engineeringen_US
dc.description.degreeBachelor of Engineering (Aerospace Engineering)en_US
dc.contributor.supervisor2Tonse Gokuldas Paien_US
item.grantfulltextrestricted-
item.fulltextWith Fulltext-
Appears in Collections:MAE Student Reports (FYP/IA/PA/PI)
Files in This Item:
File Description SizeFormat 
FYP Report.pdf
  Restricted Access
12.58 MBAdobe PDFView/Open

Page view(s) 50

450
Updated on Jul 24, 2024

Download(s)

15
Updated on Jul 24, 2024

Google ScholarTM

Check

Items in DR-NTU are protected by copyright, with all rights reserved, unless otherwise indicated.