| dc.contributor.author |
Rahman, Irfanur |
|
| dc.contributor.author |
Asaduzzaman, K. M. |
|
| dc.contributor.author |
Arman, Arif |
|
| dc.date.accessioned |
2016-08-02T04:44:51Z |
|
| dc.date.available |
2016-08-02T04:44:51Z |
|
| dc.date.issued |
2014-12 |
|
| dc.identifier.uri |
http://hdl.handle.net/123456789/245 |
|
| dc.description |
This project and dissertation is a significant outcome of supreme guidance and concentrated team effort. We respectfully acknowledge the cordial help of individuals who played distinct role for the successful accomplishment of the project. We offer our deepest gratitude to our supervisor Wg Cdr Dr G.M Jahangir Alam, psc, senior instructor; Department of Mechanical Engineering (MIST).His tremendous contribution, excellent guidance and depth of knowledge in the relevant field lead our project to a perfect completion.
We are also indebted to the faculty members of Department of Mechanical Engineering, (MIST) for the required additional support. We thank MIST for providing us with the required funding for implementing the project. We would like to express our humble gratitude to all the mechanics, technicians, and lab assistants of MIST workshop for rendering us technical support.
Last but not the least; we acknowledge the support and patience of our parents who allowed us necessary freedom during the completion of the project. Above all we praise and thank the almighty Allah for the success of the project. |
en_US |
| dc.description.abstract |
The principal objective of this project is to design and manufacture an UAV having an aerofoil shaped fuselage. The project includes potential study of the advantages of aerofoil shaped fuselage and aerofoil shaped horizontal stabilizer in an aircraft.
The manufacturing process, design factors and considerations, material selection etc are elaborately explained in this report.
The effects of aerofoil shaped fuselage and horizontal stabilizer on the lift; drag and stall are discovered to facilitate a responsive and stable control over the Unmanned Aerial Vehicle (MIST EAGLE EYE). Necessary design corrections are executed and aircraft stability is enhanced to a desired level.
Real life test flight is conducted and flight troubles are observed. The causes of flight difficulties are investigated. Finally, required design modifications are implemented to attain satisfactory real life control over the Unmanned Aerial Vehicle (UAV).
This remote control UAV titled as “MIST EAGLE EYE” is a unique addition to the list of unmanned aerial vehicle of the present time .It stands out due to its aerofoil shaped fuselage. |
en_US |
| dc.description.sponsorship |
Department of Mechanical Engineering (ME)
Military Institute of Science and Technology (MIST) |
en_US |
| dc.language.iso |
en |
en_US |
| dc.publisher |
Department of Mechanical Engineering (ME) Military Institute of Science and Technology (MIST) |
en_US |
| dc.relation.ispartofseries |
Thesis of B Sc in Mechanical Engineering; |
|
| dc.subject |
STRUCTURAL DESIGN, ANALYSIS, FLIGHT, UNMANNED AERIAL VEHICLE, AEROFOIL, SHAPED FUSELAGE |
en_US |
| dc.title |
STRUCTURAL DESIGN, ANALYSIS AND FLIGHT TEST OF AN UNMANNED AERIAL VEHICLE (UAV) HAVING AEROFOIL SHAPED FUSELAGE |
en_US |
| dc.type |
Thesis |
en_US |
