Tujuan projek ini adalah untuk membangunkan kawalan flap untuk helikopter ultraringan
berdasarkan konsep menukar aliran udara. Struktur flap kawalan dianalisis berdasarkan
kepada keadaan yang melampau. Kawalan flap terdiri daripada dua bahan-bahan iaitu
Aluminum (2014-T4) dan PF. Maksimum tegasan Von Mises diperolehi daripada
simulasi adalah 38.75MPa. Keputusan yang diperolehi daripada Analisis Unsur
Terhingga (AUT) tidak melebihi faktor keselamatan 1.5 berdasarkan keperluan kelayakan
terbang. Oleh itu struktur kawalan flap dianggap selamat dan tidak akan gagal. Untuk
pengesahan perisian AUT, kes yang mudah untuk pesongan rasuk dan plat telah
dijalankan dan dibandingkan dengan pengiraan teori. Keputusan daripada kedua-dua teori
dan AUT dibandingkan dan perbezaan adalah 3.72% dan 1.48% bagi rasuk dan plat.
Keputusan yang boleh diterima, kerana perbezaan adalah lebih rendah daripada 5%.
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The purpose of this project is to develop control flap for ultralight helicopter based on the
concept of changing the airflow. The structure of the control flap was analyzed based on
the extreme condition. The control flap consists of two materials which are Aluminum
(2014-T4) and PF. The maximum Von Mises stresses obtained from the simulation was
38.75MPa. The results obtained from FEA do not exceed safety factor of 1.5 based on
airworthiness requirement. Thus the structure of control flap is assumed to be safe and
will not fail. For verification of the FEA software, a simple case of deflection of beam
and plate were conducted and compared with the theoretical calculation. The results from
both of theoretical and FEA were compared and the differences are 3.72% and 1.48% for
beam and plate respectively. The results are acceptable since the differences are lower
than 5%.
Development of a control flap for the ultralight helicopter / Mohammad Shair Mohd Zain