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All Journal JMPM (Jurnal Material dan Proses Manufaktur) Infotekmesin
Azhim Asyratul Azmi
Universitas Muhammadiyah Yogyakarta
Computer Science & IT Electrical & Electronics Engineering Engineering Mechanical Engineering

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Simulasi Penerapan End Plate Wing Tip Devices pada Pesawat Model UAV Jenis Glider Azhim Asyratul Azmi; Wahyudi Wahyudi; Aris Widyo Nugroho
JMPM (Jurnal Material dan Proses Manufaktur) Vol 3, No 2 (2019): Desember
Publisher : Universitas Muhammadiyah Yogyakarta

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.18196/jmpm.3239

Abstract

Aliran udara yang bergerak dari tekanan tinggi ke tekanan rendah menimbulkan pusaran udara pada ujung sayap atau biasa dikenal sebagai wing tip vortices. Wing tip vortices menyebabkan downwash yang mengurangi nilai gaya angkat pada sayap. Berbagai tipe wing tip devices kemudian dirancang untuk mengurangi wing tip vortices, salah satunya adalah wing tip devices jenis end plate. Penelitian pengaruh penerapan wing tip devices dengan variasi sudut kemiringan dapat menggunakan metode pendekatan simulasi. Wing tip devices jenis end plate dirancang dengan desain mengacu pada Withcomb winglet bagian atas. Objek simulasi meliputi pesawat model glider tanpa end plate, menggunakan end plate dengan sudut kemiringan 0o dan end plate dengan sudut kemiringan 15°. Simulasi dilakukan dengan tiga variasi kecepatan jelajah 50, 60, dan 70 km/jam. Hasil simulasi menunjukkan bahwa penerapan end plate dapat meningkatkan nilai gaya angkat. Persentase peningkatan terbesar yaitu 4,1% menggunakan end plate dengan sudut kemiringan 15° pada kecepatan 70 km/jam. Persentase penurunan nilai gaya hambat terbesar terjadi pada konfigurasi end plate dengan sudut kemiringan 15° pada kecepatan 50 km/jam yaitu sebesar 1,04%. Hasil kontur dan iso surface menunjukkan bahwa penerapan end plate pada ujung sayap menjadikan distribusi tekanan lebih merata di permukaan sayap sehingga terjadi peningkatan nilai gaya angkat. Air flow moving from high pressure to low pressure produces vortex at wing tip known as wing tip vortices. Wing tip vortices generate downwash flow and reduce distribution of pressure on the wing. Many types of wing tip devices had been designed to reduce wing tip vortices effect, one of the design is known as end plate wing tip devices. Research of wing tip devices with cant angle variation can be conducted by simulation approach. The end plate wing tip devices has been designed according to the upper section of with comb winglet. The object of simulation was a glider plane model without end plate, end plate with cant angel 0° and 15°. Simulation had been observed with three variations of cruising speed: 50, 60, and 70 km/h. Simulation result shows the 15° end plate can increase 4.1% lift at 70 km/h, and reduce 1.04% drag at 50 km/h compared to wing tip without end plate. Contour and iso surface result the end plate make pressure distribution on wing pressure more uniform and generated more lift. 
Studi Numerik Kontur Pola Aliran Fluida Pendinginan Pada Mold Injeksi Molding Angger Bagus Prasetiyo; Fauzun Fauzun; Azhim Asyratul Azmi; Rizqi Ilmal Yaqin
Infotekmesin Vol 12 No 1 (2021): Infotekmesin: Januari 2021
Publisher : P3M Politeknik Negeri Cilacap

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35970/infotekmesin.v12i1.493

Abstract

The conventional cooling process was chosen because of the better estimation of manufacturing times and lower manufacturing costs. One alternative to minimize the decline in quality in plastic products is by using a conformal cooling process. This study will compare the contours of the fluid flow pattern between conventional cooling channels and conformal cooling channels. Case study on a box-shaped product made of PP material which has a melt temperature of 205 ° C. 3D product images were made with Solidwork 2017 software and process simulation using fluent 19.0 software. The results showed that the temperature flow pattern in the conformal channel resulted in a temperature absorption of around 303.2K while the conventional cooling channel was around 302.5K. Then the coolant channel that experiences high pressure drop occurs in the conformal cooling channel around 88888.9 pascals and the conventional cooling channel around 355555.6 pascals.
Perancangan Sistem Autonomous pada Pesawat Model UAV Jenis Glider Azhim Asyratul Azmi; Wahyudi Wahyudi
JMPM (Jurnal Material dan Proses Manufaktur) Vol 3, No 1 (2019): Juni
Publisher : Universitas Muhammadiyah Yogyakarta

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.18196/jmpm.3134

Abstract

AbstrakPesawat model jenis glider merupakan pesawat yang mampu terbang dangan kecepatan rendah dan memiliki efisiensi tinggi dalam penggunaan sumber daya tenaga yang digunakan, sehingga banyak digunakan untuk misi pemantauan. Misi pemantauan menggunakan pesawat glider memiliki keterbatasan. Pilot sebagai ahli kemudi pesawat memiliki keterbatasan jarak pandang, sehingga misi pemantauan yang dilakukan hanya sebatas jarak pandang pilot itu sendiri. Untuk meningkatkan luas area pemantauan, pesawat harus dapat terbang secara mandiri atau biasa disebut dengan aotonomous. Pesawat model yang mampu terbang secara autonomous disebut dengan pesawat model Unmanned Aerial Vehicle (UAV). Paenerapan sistem autonomous pada pesawat model UAV dilakukan dengan menggunakan perangkat autonomous berupa flight controller, GPS, software GCS dan telemetri. Pemilihan perangkat autonomous disesuaikan terhadap spesifikasi pesawat model Solfix yang meripan pesawat model jenis glider untuk pemantauan titik api kebakaran hutan. Pemberian parameter atur yang merupan kontrol PID dilakukan dengan metode eksperimen uji terbang secara langsung. Nilai parameter atur diperoleh dari observasi yang dilakukan terhadap pergerakan pesawat ketika auto mode. Waypoint uji terbang berbentuk persegi dengan jarak 500m untuk setiap sisi.Pesawat model Solfix dapat terbang secara autonomous dengan stabil melewati waypointyang ditentukan. AbstractGlider model airplane is an aircraft model with low speed cruising capability and high energy efficiency, widely used for observation missions. The main problem of using glider model plane to observation missions is the limitation of pilot visibility. Glider model airplane must be able to fly autonomously that also known as Unamanned Aerial Vehicle (UAV) to increase observation area futher. Implimitation of autonomous system on glider model airplane can be carried out by applying flight controller, GPS, GCS software and telemetry. Autonomous system was applied and adjusted to glider model airplane called Solfix. Arduflyer 1.5 Flight controller was used in this topic with flight test experimental approach to reach flight setup and tuning. Rectangle shape waypoint was set up with 90 m width and 100 m long. The flying set up and tuning was reached by observed airplane movement behavior on auto mode to follow the waypoint. Solfix model airplane was successfully flown on auto mode by following the waypoint with flight tuning: RLL2SRV_P=1,5;RLL2SRV_D=0,1;PTCH2SRV_P=1,5; PTCH2SRV_D =0,12; YAW2SRV_RLL=1,0; YAW2SEV_DAMP=0,3 and Rudder Mix=0,250.       
Co-Authors Angger Bagus Prasetiyo Aris Widyo Nugroho Fauzun Fauzun Rizqi Ilmal Yaqin Wahyudi, Wahyudi