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Eagle wing design/Lee Chunhow

Eagle wing design_Lee Chunhow_A2_2009_NI
Satu mekanisme bersayap kepak dengan ‘span’ variasi yang menyerupai helang telah direka bentuk dalam projek ini. Kinematik sayap yang menyerupai burung, bersama dengan motor/kotak gear yang diperlukan telah divisualisasi dengan perisian CAD. Putaran motor telah ditukar kepada gerakan linear oleh ‘driving linkage’ yang menghasilkan kepakan sayap yang beterusan. Struktur sayap kepak ini menpunyai satu darjah bebas (1 DOF) dan gerakannya adalah pada ‘spar joint’. Ia telah difabrikasi selanjutnya kepada prototaip dengan menggunakan bahan-bahan yang sesuai. Dengan bantuan ‘wind tunnel’, ciri-ciri daya angkatan model tersebut telah diuji dan dianalisa pada sudut serangan, kelajuan angin dan frekuensi kepak yang berbeza. Model tersebut telah diuji pada lingkungan parameter sehingga 15o sudut serangan, 10.8m/s kelajuan angin dan 3.185Hz frekuensi. keputusan ujian tersebut menunjukan daya angkatan meningkat sejajar dengan kenaikan sudut serangan, halaju angin dan frekuensi kepak. Walau bagaimanapun, dengan kuasa motor yang terhad, frekuensi kepak yang lebih tinggi tidak dapat diuji dan daya angkatan yang maksima tidak dapat ditentukan. Oleh itu, motor yang lebih kuasa diperlukan untuk menentukan daya angkatan optimum yang dapat dihasilkan oleh model ini. ______________________________________________________________________________________ A wing flapping mechanism with span variation analogous to eagle wing was developed in this project. The flapping motion which imposes the required kinematics was designed according to the bird flapping mechanism with the corresponding motor driven/gearbox mechanism and visualized using CAD software. The rotary motion of motor is converted to linear motion by driving linkage to provide a continuous bird-like wing flapping motion. The 1 DOF flapping wing structure, which flap about the spar joint was further developed and fabricated into prototype with appropriate materials. Based on the model, the lift characteristics of flapping flight were investigated by testing at various angles of attack, wind tunnel speeds and flapping frequencies with the aids of wing tunnel. The model was tested at a range of parameters up to 15o angle of attack, 10.8m/s wind speed and 3.185Hz frequency. Lift characteristic of the flapping wing responding proportional to angle of attack, wind speed and flapping frequency. However, due to the motor power constraint, higher frequencies testing were not performed and the maximum available lift of this particular model was undetermined. Therefore, a bigger motor is needed in order to determine the optimum lift performance of this model.
Contributor(s):
Lee Chunhow - Author
Primary Item Type:
Final Year Project
Language:
English
Subject Keywords:
wing flapping; span; prototype
First presented to the public:
4/1/2009
Original Publication Date:
5/23/2019
Previously Published By:
Universiti Sains Malaysia
Place Of Publication:
School of Aerospace Engineering
Citation:
Extents:
Number of Pages - 70
License Grantor / Date Granted:
  / ( View License )
Date Deposited
2019-05-23 10:30:40.925
Submitter:
Nor Hayati Ismail

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