Article Per Year (5 Year)
p-Index From 2021 - 2026
1.908
P-Index
This Author published in this journals
All Journal ELKHA : Jurnal Teknik Elektro Jurnal Teknologi Elektro Jurnal Abdimas BSI: Jurnal Pengabdian Kepada Masyarakat Journal of Research and Technology Conference SENATIK STT Adisutjipto Yogyakarta CHEESA: Chemical Engineering Research Articles Angkasa: Jurnal Ilmiah Bidang Teknologi Compiler KACANEGARA Jurnal Pengabdian pada Masyarakat Aviation Electronics, Information Technology, Telecommunications, Electricals, Controls (AVITEC) Abdimas Galuh: Jurnal Pengabdian Kepada Masyarakat Vortex Jurnal Peradaban Masyarakat (JPM) Jurnal Manajemen dan Teknologi Rekayasa Jurnal Teknologi Maritim Jurnal Teknologi Maritim
Denny Dermawan
Department of Electrical Engineering, Sekolah Tinggi Teknologi Adisutjipto
Aerospace Engineering Agriculture, Biological Sciences & Forestry Chemical Engineering, Chemistry & Bioengineering Chemistry Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Decision Sciences, Operations Research & Management Earth & Planetary Sciences Economics, Econometrics & Finance Education Electrical & Electronics Engineering Energy Engineering Environmental Science Industrial & Manufacturing Engineering Law, Crime, Criminology & Criminal Justice Materials Science & Nanotechnology Mechanical Engineering Nursing Public Health Social Sciences

Published : 26 Documents Claim Missing Document
Claim Missing Document
Check
Articles

Found 26 Documents
Search

 1   2   3 
Robust Stability of Sliding Mode Control for Pitch Attitude Boeing 747 Aircraft System Setiawan, Paulus; Matuan, Lorenso Oldiardo; Astuti, Yenni; Sudibya, Bambang; Dermawan, Denny; Kurniawan, Freddy; Lasmadi, Lasmadi
Angkasa: Jurnal Ilmiah Bidang Teknologi Vol 17, No 2 (2025): November
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.28989/angkasa.v17i2.3074

Abstract

Modern aircraft have experienced rapid development at this time, which is proven by the discovery of more complex systems on aircraft. One of the systems that has experienced rapid development is the autopilot, which can control the aircraft automatically. The design of the pitch attitude system begins by collecting data on the longitudinal motion of the aircraft, which is then converted into a mathematical equation of the transfer function for the pitch motion. After the pitch attitude instability is identified, a compensator is made to improve the stability of the pitch motion, with the compensator used in this study being the lead compensator. The main objective of this study is to create a system that can identify parameter values on the Luenberger Observer control and sliding mode control (SMC) in the flight control system. The results of several test experiments clearly show that the proposed SMC controller can produce better and more stable system performance. 
Analisa kegagalan sistem beta pesawat Grob G 120TP-A dengan menggunakan metode Mean Time Between Failure Prakoso, Agung; Setyo, Bima Candra Gautama Adi; Dermawan, Denny; Budiono, Cyrilus Sukaca; Lukito, Indro; Kurniawan, Riski
JUMANTARA: Jurnal Manajemen dan Teknologi Rekayasa Vol 3, No 2 (2024): Juli
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.28989/jumantara.v3i2.2378

Abstract

Pesawat Grob G 120TP-A merupakan jenis pesawat latih dengan engine single turbo propeller. Dalam kinerja engine pesawat Grob G 120TP-A tersebut memiliki komponen yang dinamakan sistem beta untuk mengubah sudut riverse pada propeller dan menghasilkan gaya drag. Rata-rata kegagalan sistem beta banyak terjadi sebelum mecapai usia 3000 jam terbang. Berdasarkan hal tersebut dilakukan observasi kegagalan sistem beta pesawat Grob G 120TP-A dalam kurun waktu tahun 2016-2023, kemudian dilakukan analisis dengan Mean Time Between Failure (MTBF) dan dibandingkan dengan nilai probabilitas yang didapatkan dari pengalokasian Fault Tree Analysis (FTA). Hasil dari nilai mean time between failure paling tinggi pada sistem beta adalah terjadinya kegagalan N2 Fluctuate yang bernilai 961 cycle dan pesawat dengan nilai paling tinggi adalah pada pesawat LD 1201 dengan nilai 157 cycle, selanjutnya dibandingkan dengan probabilitas faul tree, maka kegagalan pada sistem beta dari total keseluruhan yang tidak bisa diterima hanya pada kegagalan vibration dan N2 fluctuate.
Rancang Bangun Receiver Automatic Dependent Surveillance Broadcast (ADS-B) Menggunakan RTL-SDR R820T2 Flight Aware Dermawan, Denny; Setiawan, Paulus; Wahyudin, Wahyudin; Widyastuti, Diah Suwarti
Jurnal Teknologi Elektro Vol 14, No 3 (2023)
Publisher : Electrical Engineering, Universitas Mercu Buana

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.22441/jte.2023.v14i3.006

Abstract

Teknologi radar pada bandar udara mulai tergantikan oleh sistem Automatic Dependent Survaillance Broadcast (ADS-B) karena ketidakmampuan radar dalam mendeteksi pesawat yang tertutup awan tebal, untuk menggantikan fungsi radar di beberapa bandar udara masih menggunakan situs Flightradar24 sebagai sumber informasi karena untuk membangun sebuah stasiun ADS-B membutuhkan biaya yang mahal. Akan tetapi Flightradar24 memiliki beberapa kelemahan, diantaranya adalah pengguna diharuskan untuk membayar atau berlangganan secara berkala jika ingin menampilkan informasi lebih detail, dan delay karena pemrosesan data yang membutuhkan akses koneksi internet. Receiver ADS-B bekerja dengan menunggu dan menerima transmisi dari pesawat terbang yang berisi informasi posisi pesawat secara berkala, dalam merancang receiver ADS-B ini peneliti menggunakan jenis RTL-SDR R820T2 Flight Aware dengan nilai gain sebesar 19 dB, dan penambahan antena ADS-B 1090 MHz. Hasil pengujian rancangan receiver ADS-B yaitu, receiver mampu menerima sinyal dan data parameter target ADS-B dengan jarak jangkauan sejauh 353 km pada range software adsbSCOPE dan 346,89 km secara perhitungan menggunakan metode harvesine formula.
ANALISIS POTENSI DAN DAMPAK KEBOCORAN GAS HIDROGEN PADA HYDROGEN PLANT DI INDUSTRI PELUMAS Setiawan, Adhi; Hanifah, Dian Nur; Nugroho, Agung; Dermawan, Denny
Journal of Research and Technology Vol. 3 No. 2 (2017): JRT Volume 3 No 2 Des 2017
Publisher : 2477 - 6165

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55732/jrt.v3i2.237

Abstract

The increasing need of industrial pure hydrogen is growing. One of its roles is petroleum industry purification. High purity hydrogen (99.99%) was obtained from methane using Steam Methane Reforming Method in hydrogen plant unit. Hydrogen is a very dangerous chemical element with its flammable characteristic. This research was conducted especially on purification system. Quantitative analysis was used to determine hydrogen leakage frequency, consequence modeling, and risk estimation that would be risen. The analysis results showed that the highest frequency occured in unignited release events. Jet fire scenario produced the longest fire length in HPU for about 27 meters. Jet fire scenario impact produced the farthest secure distance in case of a leakage in HPU section of 60 meters. Flash fire produced the farthest distance loss in a leakage case in HPU of 80 meters, and explosion at 200 meters radius would will have a blast overpressure 7.62 psig with 22% fatality estimation of the population. Keywords: Hydrogen Purification Unit, Hydrogen, Consequence Modeling, Risk.
Design and Implementation of 12-Bit Arithmetic Logic Unit with 8 Operation Codes to Field Programmable Gate Array Sumari, Arwin Datumaya Wahyudi; Hijriana, Sukriya; Dermawan, Denny
ELKHA : Jurnal Teknik Elektro Vol. 15 No.2 October 2023
Publisher : Faculty of Engineering, Universitas Tanjungpura

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.26418/elkha.v15i2.64041

Abstract

Digital system has been a part of human life since the invention of the computer with a microprocessor as the central brain. At the heart of a processor is an Arithmetic Logic Unit (ALU) that handles arithmetic and logic operations. The need for high-speed computation to handle complex computations demands microprocessors with higher performance. The existing 4-opcode 8-bit ALU cannot handle multiplication operations, so a solution is needed. In this research, while raising the appeal of beginners, a 12-bit ALU with eight operation codes (opcode) was designed and implemented in Xilinx"™s Field Programmable Gate Array using a schematic diagram approach through logic gates. The designed and implemented ALU provides addition, subtraction, multiplication, square, AND, OR, NAND, and XOR operations. The multiplication operation was tested by performing the computation to provided datasets to obtain the distance travelled by ten military aircraft based on their maximum speed and air travel duration to ensure its performance. The computation performance comparison with an 8-bit ALU with four opcodes was also done. The computation was done for air travel between 10 to 60 minutes with a 10-minute difference. It was found that the 12-bit ALU with eight opcodes outperformed its contender with computation differences between 130.815 ns and 1,468.214 ns. This high performance is supported by the multiply operation that does repeated addition at one time. Based on this finding, the 8-opcode 12-bit ALU is more efficient in the context of computation time, with consistent accuracy. Moreover, the computation time required to calculate military aircraft data with different maximum speeds and air travel duration is only 119.501 ns.
SENSOR SYSTEM DESIGN FOR PROPELLER TEST BENCH Ihsan, Nurul; Dermawan, Denny; P, Lazuardy Rahendra
Vortex Vol 2, No 2 (2021)
Publisher : Institut Teknologi Dirgantara Adisutjipto

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1147.43 KB) | DOI: 10.28989/vortex.v2i2.1006

Abstract

The sensor system is a system that functions to detect signals that come from changes in energy such as electrical energy, physical energy, chemical energy, biological energy, mechanical energy, and so on. The propeller test bench is an propeller performance testing platform prior to propeller installation on an aircraft to ensure engine suitability. The purpose of this design is to test the performance capability of the engine with the right sensor system measurement tool so that it can generate the value of thrust, rpm speed, and the temperature of an engine which will be designed to be used in the learning process to support propulsion practicum activities. The method used in this research is an experimental method of sensor system design. The design of the sensor system consists of a tachometer as a rpm measurement sensor, a thermostat as a sensor to measure the temperature of the propeller spool and temperature of the engine fin, and also a load cell as a sensor to measure the thrust value.The sensor system test results were then validated using the measurement results by the sensor manufacturer. The test was carried out on a wood-type propeller measuring 22 x 8 chords 4,5 cm and 5 cm. Based on the test results, it is known that the chord wood type propeller is 4,5 cm, at the maximum rpm is 7021.7, the resulting thrust value is 6.75. In testing the 5cm chord wood type propeller shows the maximum speed of 6977.5 produces a thrust of 6.95. Validation was carried out on the measurement results of rpm and thrust, the average error factor obtained for 4,5 cm chord wood type propeller was 0.783%, while for 5 cm chord wood type propeller the average error factor obtained was 1.0582%. From the resulting average error, it can be concluded that the measuring instrument for this sensor system has good accuracy
Co-Authors Adhi Setiawan Agung Prakoso Alam, Hermansyah Arif Basuki Arwin Datumaya Wahyudi Sumari Ayu Febriyanti, Ayu Bambang Sudibya, Bambang Benedictus Mardwianta, Benedictus Budiono, Cyrilus Sukaca Catur Budi Waluyo, Catur Budi Diah Suwarti Widyastuti Firmansyah, Andika Agung Firmansyah, Bagas Wahyu Freddy Kurniawan Hanifah, Dian Nur Hidayat, Zhulfa Arif Hijriana, Sukriya Ihsan, Nurul Irawan, Wahyu Jarita Dewi, Vivia Mustaqimah Jayawarsa, A.A. Ketut Jusoh, Muzammil Krisna, Angga Leo Anggara Kurniawan, Wahid Lasmadi, Lasmadi Lukito, Indro Luqman Ashari, Moch. Matuan, Lorenso Oldiardo Muhamad Jalu Purnomo, Muhamad Jalu Muhammad Jalu Purnomo, Muhammad Jalu Muminov, Bahodir Nindyapuspa, Ayu Novi Eka Mayangsari Nugroho, Agung Nurcahyani Dewi Retnowati P, Lazuardy Rahendra Pakpahan, Araya Bonita Pradnjaparamitha, Intan Dyah Purnami, Ndaru Atmi Purnomo, M. Jalu Putra, Maesa Agny Manggala Rahmawati, Fajar Khanif Riski Kurniawan Setiawan, Paulus Setyo, Bima Candra Gautama Adi Sidik, Aden Ilyas Talent Nia Pramestyawati Urzais, Mazdra Wahyudin Wahyudin Wijanarko, Sidiq Yenni Astuti, Yenni Yuliani Indrianingsih