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All Journal Jurnal Teknosains JTT (Jurnal Teknologi Terapan) Industrial Research Workshop and National Seminar
Wibowo, Singgih Satrio
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Humanities Biochemistry, Genetics & Molecular Biology Chemical Engineering, Chemistry & Bioengineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Education Electrical & Electronics Engineering Engineering Industrial & Manufacturing Engineering Mechanical Engineering Other

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Rancang Bangun Miniatur Alat Peraga Control Surface Pesawat Fixed Wing Cessna 172 Skyhawk Darmawan, Shinu Prabu Dwi Putra; Wibowo, Singgih Satrio
Prosiding Industrial Research Workshop and National Seminar Vol 14 No 1 (2023): Vol 14 (2023): Prosiding 14th Industrial Research Workshop and National Seminar
Publisher : Politeknik Negeri Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35313/irwns.v14i1.5421

Abstract

Pesawat Cessna 172 Skyhawk merupakan pesawat kecil dengan kapasitas 4 orang, pesawat ini dapat bergerak karena adanya sistem control surface. Tujuan dari perancangan ini adalah membuat miniatur control surface pesawat Cessna yang tujuannya untuk mempermudah memahami bagaimana garak pesawat ketika mengudara dengan mengimplestasikan sistem flight control yang sebenarnya pada miniatur pesawat dengan menggunakan sistem komponen Arduino dan Potensiometer sebagai pengatur pengendalian. Untuk tercapainya pembuatan miniatur alat peraga control surface pesawat Cessna 172 Skyhawk menggunakan 2 metode yaitu metode analisis dan metode eksperimental. Metode analisis terdiri beberapa tahapan yaitu, studi literatur, pembuatan desain, dan penentuan bahan. Metode eksperimental yaitu perancangan, manufaktur, uji coba, dan pembuatan laporan. Hasil yang diperoleh dari perancangan ini adalah sebuah miniatur alat peraga control surface pesawat Cessna 172 Skyhawk perancangan ini diharapkan bisa menjadi sebuah fasilitas media belajar untuk mahasiswa dan dosen program studi Teknik Aeronautika khususnya pada matakuliah praktik sistem pesawat udara 2.
Rancang Bangun Platform Gerak Untuk Simulator Pesawat Udara : Kajian Dan Perancangan Rangkaian Listrik Dan Elektronika Abhinaya, Muhammad Adam; Salim, Yusuf; Firmansyah, Pajar; Wibowo, Singgih Satrio
Prosiding Industrial Research Workshop and National Seminar Vol 15 No 1 (2024): Prosiding 15th Industrial Research Workshop and National Seminar (IRWNS)
Publisher : Politeknik Negeri Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.35313/irwns.v15i1.6198

Abstract

Artikel ini menjelaskan tentang perancangan dan konstruksi platform gerak untuk simulator pesawat udara, platform ini bertujuan untuk memberikan pengalaman simulasi realistis dalam penerbangan pesawat terbang. Motor wiper dipilih sebagai elemen utama sistem ini karena memiliki fungsi kinematik serta rekayasa kerja yang dapat mensimulasikan kondisi gerak yang berbeda-beda, layaknya sebuah servo. Selama tahap desain, komponen dan perangkat keras dipilih sesuai dengan kebutuhan simulasi. Motor Wiper dipasang ke platform dan menghasilkan gerakan rotasi, serta pengontrol khusus digunakan untuk mengendalikan pergerakan platform. Sistem kendali dikembangkan menggunakan algoritma yang dapat mensimulasikan kondisi gerak 3 derajat kebebasan, yaitu rolling, pitching dan yawing. Platform ini juga dilengkapi dengan sensor untuk mengukur perubahan posisi dan orientasi, data yang diperoleh sensor ini digunakan sebagai umpan balik untuk meningkatkan akurasi gerakan. Platform simulasi gerak ini diharapkan dapat dimanfaatkan oleh mahasiswa dalam simulasi gerak pesawat saat penerbangan, serta aplikasi lain yang memerlukan simulasi gerak 3D. Keseluruhan proyek menggabungkan aspek teknik mekatronika, kontrol, dan pemrosesan sinyal untuk menciptakan platform simulasi gerak yang efektif dan andal.
MALE UAV LONGITUDINAL STABILITY DETERMINATION USING WIND TUNNEL DATA Adhynugraha, Muhammad Ilham; Megawanto, Fadli Cahya; Octaviany, Siti Vivi; Budiarti, Dewi Habsari; Muliadi, Jemie; Nami, Osen Fili; Wibowo, Singgih Satrio
Jurnal Teknosains Vol 14, No 1 (2024): December
Publisher : Universitas Gadjah Mada

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.22146/teknosains.89420

Abstract

Unmanned aerial systems have been increasing in demand for a wide range of operations, including the rapid growth of advanced navigation and communication. One of the most important things in designing an Unmanned Aerial System (UAS) is to ensure the system's stability, such as the UAS itself. This study was conducted on an in-house medium altitude long endurance (MALE) UAS aircraft. It is focused on analyzing the longitudinal stability of MALE UAS. A mathematical approach was used to analyze the longitudinal stability.  A series of wind tunnel tests using a scaled model of the MALE UAS is done to produce several sets of data containing longitudinal stability derivatives for various configurations. A few sets of data are chosen to obtain the stability derivatives needed. These stability derivatives are utilized to determine the longitudinal motion characteristic of the aircraft. The analysis of certain derivatives and the phugoid and short-period mode shows that the aircraft is statically and dynamically stable in longitudinal motion. The results indicated that a weight change prompted an altercation in the natural frequency of the short-period mode. The response also showed that reaching a new equilibrium state takes a rather long period after an arbitrary perturbation is initiated. The time required to subdue oscillation in axial and average velocities is more than 100 seconds. The stability in the pitch rate is reached in around 65 seconds. The time to reach stability in pitch angle response is around 65 seconds.
RANCANG BANGUN ALAT UKUR GAYA DORONG DAN MOMEN UNTUK PROPELER UAV KECIL: KAJIAN SUBSISTEM Wibowo, Singgih Satrio; Luthfi, Mochammad; Rosalia, Citra Asti
Jurnal Teknologi Terapan Vol 11, No 1 (2025): Jurnal Teknologi Terapan
Publisher : P3M Politeknik Negeri Indramayu

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.31884/jtt.v11i1.712

Abstract

Thrust and Moment Meter (TMM) is an instrument for measuring thrust and moment or torque produced by a small electric propulsion system, which is usually used on Unmanned Aerial Vehicles (UAV) and/or small size Radio Control (RC) aircraft. This tool is designed with low-cost materials and simple process, namely Acrylonitrile Butadiene Styrene (ABS) plastic using 3D printing technology. The main component of this device is an Arduino Nano microcontroller, equipped with three Load Cell sensors and one LCD screen. The results of this research are that the TMM tool has been successfully created and tested for accuracy in several cases, and very good results were obtained where the force measurement accuracy was more than 99% (error < 1%).
PENGEMBANGAN KENDALI TERBANG BERBASIS SLIDING MODE CONTROL DENGAN ELIMINASI CHATTERING PADA QUADROTOR UNTUK MENGATASI GANGGUAN ANGIN TAK TENTU DI KAWASAN JAWA BARAT Zuhri, Muhammad Rizki; Wibowo, Singgih Satrio; Soetanto, Maria Fransisca
Jurnal Teknologi Terapan Vol 10, No 2 (2024): Jurnal Teknologi Terapan
Publisher : P3M Politeknik Negeri Indramayu

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.31884/jtt.v10i2.677

Abstract

Quadrotors are intrinsically unstable. If there is a sudden wind disturbance, this wind disturbance will be amplified so that the quadrotor's attitude becomes uncontrollable. West Java is one of the regions in Indonesia that has quite high wind disturbances. The recorded daily wind disturbance reached 6.99 m/s with a maximum value of 9.95 m/s. In this research, a control system based on the sliding mode control (SMC) algorithm is used. The advantage of this control algorithm is its ability to compensate for uncertain disturbances. This research investigates the implementation of the SMC control into a quadrotor by incorporating random wind disturbance aspects into the model. The research was carried out numerically with simulations using MATLAB/Simulink, with the position variables being the main focus. Quadrotor equipped with SMC has a lower mean error value for the desired position relative to the real position. This shows that the SMC control algorithm that has been created is able to properly overcome random wind disturbances that occur in the West Java area.
Co-Authors Abhinaya, Muhammad Adam Adhynugraha, Muhammad Ilham Budiarti, Dewi Habsari Citra Asti Rosalia Darmawan, Shinu Prabu Dwi Putra Firmansyah, Pajar Luthfi, Mochammad Megawanto, Fadli Cahya Muliadi, Jemie Nami, Osen Fili Octaviany, Siti Vivi Salim, Yusuf Soetanto, Maria Fransisca Zuhri, Muhammad Rizki