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dc.contributor.authorTan, Chun Sing.
dc.description.abstractMorphing wings are the subject of intensive research interest today due to their potential to improve aircraft versatility for multiple mission requirements. This report focuses on the development of a morphing UAV model with variable wing camber which is able to transform between airfoil NACA23015 with E423. The morphing mechanism is designed and fabricated, and to be actuated by electrical servo motors. These changing in airfoil profile allow the UAV to maximize lift during take-off and landing, while minimizing drag during cruising. The morphing mechanism is carefully evaluated and tested, all the critical supporting structures are being analyzed using the finite element method, to ensure that the UAV is able to sustain under the designed loading parameters. Despite the variable camber, the UAV also incorporate the feasibility of variable swept wing for future research purposes. The wing box is built to include the variable swept wing mechanism, and the 3 points flexural test is conducted on the wing box structure, to ensure that the wing box is able to withstand the moment generated by the wings. Next, the fuselage of the UAV is built, which includes the selection and evaluation of motor as well as installation of landing gears. Finally, test fly is conducted to study the improvement of flying characteristic that brought by the morphing wings.en_US
dc.format.extent99 p.en_US
dc.rightsNanyang Technological University
dc.subjectDRNTU::Engineering::Mechanical engineeringen_US
dc.titleDevelopment of morphing UAVen_US
dc.typeFinal Year Project (FYP)en_US
dc.contributor.supervisorJorg Uwe Schluteren_US
dc.contributor.supervisorLiu Yongen_US
dc.contributor.schoolSchool of Mechanical and Aerospace Engineeringen_US
dc.description.degreeBachelor of Engineering (Mechanical Engineering)en_US
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Appears in Collections:MAE Student Reports (FYP/IA/PA/PI)
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