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Implementation of UAV design into CAD
Mälardalen University, School of Innovation, Design and Engineering.
2011 (English)Independent thesis Basic level (professional degree), 10 credits / 15 HE creditsStudent thesis
Abstract [sv]

SAMMANFATTNING

Detta arbete har gått ut på att i CAD implementera en UAV-design av Enebog, Designen har förmedlats av handledaren via möten och mail. Ett ”levande” dokument skapades och har sedan uppdaterats från båda sidor genom projektets fortlöpande. Dimensioner och mått har diskuterats samt hur det ska implementeras i CAD. UAV’n är uppbyggd som en ”assembly” i CAD, med tillhörande modeller och ”sub-assemblies”. Modellerna är designade i Solid Works standard-arbetsbänk och ihopsatta i assemblyn med så kallade ”mates”. Tyngdpunkt och massa har beräknats i Solid Works för flygplanets olika delar. Datat har exporterats till Excel för att kunna presenteras.

Resultatet är 7 stycken 2D ritningar kopplade till en 3D modell. Flygplanet har en spännvidd på 2,7 meter och en vingarea på 0,91m2. Den totala längden dimensionerades till 1,87 meter och den totala massan kalkylerades till 8,68 kg, som också är flygplanets ”take off weight”. Flygplanet är designat för att byggas med två olika komposit material: kolfiber/epoxy och glasfiber/epoxy. I ritningsunderlaget genererares tre-plans vyer med måttsättning, detaljvyer på till exempel nos-poden i den främre delen av flygplanet samt en sprängskiss med innehållsförteckning.

Abstract [en]

ABSTRACT

This work has been focused on implementing, into CAD (Solid Works), a UAV-design by Enebog. The design has been given to the author on meetings and mail. A “living” document with design parameters was updated from both sides continuously throughout the project. The measurements/dimensions of the aircraft were discussed as well as how to implement in CAD. All updates were also continuously updated in the document. The UAV is built up as an assembly in CAD, with sub-assemblies and parts. The parts are designed with the standard work bench in Solid Works and mated together to form an aircraft. Center of gravity and mass properties of the parts were calculated in Solid Works and exported to Excel for the purpose of presenting the data.

The result is 7 2D drawings attached to a 3D model. The aircraft has a wing span of 2,7 meters (8,68 ft), with a corresponding wing area of 0,91 m2 (9,8 ft2). The total length is dimensioned to 1,87 m (6,14 ft) and the total mass is calculated to 8,68 kg (19,14 lbs), which is also the aircrafts takeoff weight. The aircraft is designed to be built with two composite materials; carbon fiber/epoxy and glass fiber/epoxy. In the drawing material plan views with dimensions of the aircraft, detail views of e.g. the nose pod in the front part of the aircraft, an exploded view with a corresponding build of material-table was generated.

Place, publisher, year, edition, pages
2011. , 33 p.
National Category
Vehicle Engineering
Identifiers
URN: urn:nbn:se:mdh:diva-12322OAI: oai:DiVA.org:mdh-12322DiVA: diva2:419506
Subject / course
Aeronautical Engineering
Uppsok
Technology
Supervisors
Available from: 2011-06-01 Created: 2011-05-26 Last updated: 2011-06-01Bibliographically approved

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Boman, David
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