Kepentingan dalam membina pesawat udara tanpa pemandu (UAV) hibrid meningkat secara intensif kerana keupayaan untuk melaksanakan operasi konfigurasi pelepasan dan pendarat menegak, selain daripada mod penerbangan ke hadapan. Dengan keupayaan tersebut, UAV hibrid amat diperlukan di pelbagai industri seperti tentera, pertanian, dan geografi. Malangnya, UAV hibrid menghadapi cabaran-cabaran tertentu seperti keadaan angin yang kuat semasa hover, kerumitan analsis rejim penerbangan peralihan, dan pengeluaran prototaip yang kos tinggi. Dengan mengambil kira, pesawat udara tanpa pemandu yang bersayap tetap direka dan dibangunkan dengan sedikit tumpuan sepanjang keseluruhan projek. Reka bentuk dioptimumkan untuk mencapai prestasi penerbangan terbaik dari segi penganggaran berat, aerodinamik, sistem pendorongan, dan kestabilan dan kawalan dengan menggunakan Matlab, XFLR5, dan reka bentuk bantuan komputer seperti SolidWorks. Dengan masa yang diperuntukkan dan sokongan kewangan, prototaip kos rendah dibuat berdasarkan hasil yang dioptimumkan. Proses lay-up telah diintegrasikan ke dalam fabrikasi prototaip untuk memastikan struktur yang mempunyai kekuatan tinggi. Seterusnya, percubaan penerbangan menunjukkan bahawa UAV tersebut yang dikawal secara manual boleh berlepas secara menegak dengan penerbangan yang tidak stabil. Oleh itu, kemungkinan langkah seterusnya adalah untuk mereka alat pengawalan yang membolehkan UAV tersebut dikawal secara autonomi untuk mencapai prestasi pernerbangan yang terbaik.
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The interest in building hybrid Unmanned Aerial Vehicles (UAVs) are increasing intensively due to its capability to perform Vertical Take-Off and Landing (VTOL), in addition to the forward flight mode. With the capability, the hybrid UAVs are highly on demand in various industries such as military, agricultural, and geographic. Unfortunately, hybrid UAVs are facing certain challenges such as the strong crosswind condition during hover mode, complexity in transition flight regime analysis, and the high-cost prototype manufacturing. Taking the challenges into consideration, the fixed-wing VTOL UAV was designed and developed with few focuses during the entire process. The design was optimized to achieve the best flight performance in terms of weight estimation, aerodynamic, propulsion, and stability and control by using Matlab, XFLR5, and Computer Aided Design (CAD) such as SolidWorks. With the allocated time and financial support, a low-cost prototype was developed and fabricated according to the optimized result. Lay-up process was integrated into the prototype fabrication to ensure the high strength structure. Next, testing in actual conditions was needed that led the prototype to flight test. The fixed-wing VTOL UAV was able to take-off vertically with an unstable flight that controlled manually. Therefore, possible next step is to design a controller that allows the fixed-wing VTOL UAV to be controlled and stabilized autonomously in order to achieve the best flight performance.
Design and development of a fixed-wing vertical take-off and landing unmanned aerial vehicle / Lester Wong Seng Man