Article Per Year (5 Year)
p-Index From 2020 - 2025
1.503
P-Index
This Author published in this journals
All Journal Jurnal Ilmu Dasar Warta Ardhia : Jurnal Perhubungan Udara Computational and Experimental Research in Materials and Renewable Energy (CERiMRE) Indonesian Journal of Aerospace
Wijaya, Yusuf Giri
Unknown Affiliation
Aerospace Engineering Astronomy Computer Science & IT Control & Systems Engineering Energy Materials Science & Nanotechnology Mathematics Physics Transportation

Published : 8 Documents Claim Missing Document
Claim Missing Document
Check
Articles

Found 8 Documents
Search

 1 
Analysis of Vibration in Payload Room Due to Engine Vibration on LSU-05 NG Wijaya, Yusuf Giri; Ula, Nur Mufidatul; Muksin, M.; Pratama, Mukhael Gilang Pribadi Putra
Computational And Experimental Research In Materials And Renewable Energy Vol 4 No 1 (2021): May
Publisher : Physics Department, Faculty of Mathematics and Natural Sciences, University of Jember

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.19184/cerimre.v4i1.24963

Abstract

LSU-05 NG is one of the unmanned air vehicles (UAV) developed by the aviation technology center LAPAN. The LAPAN aviation technology center designed the LSU-05 NG to be able to carry a larger payload and broader range than other types of LSUs. Therefore, the LSU-05 NG uses an engine that has enough power. LSU-05 NG uses a piston-type engine with a capacity of 170 CC. UAV engine is the primary source of vibration in the UAV structure. Excessive vibration can cause damage to the UAV structure and malfunction of the UAV payload, such as sensors, control systems, and cameras. In this research, vibration measurements were carried out at 2 locations. The measurement location is on the engine and where the payload is installed. The vibration measurement on the LSU-05 NG was carried out during the ground test. The accelerometer sensor is used to measure vibrations and is connected to the NI data acquisition system and displayed with LabVIEW. The data to be taken are acceleration and frequency data with variations in the RPM value on the LSU-05 NG engine. With these measurements, the vibration characteristics caused by the engine in the LSU-05 NG structure, primarily where the payload is stored, can be known.
Vibration Test Fixtures Design for Payload of Tubular Telemetry System Muksin, Muksin; Pratama, Mikhael Gilang Pribadi P.; Nugroho, Yudha Agung; Wijaya, Yusuf Giri; Ula, Nur Mufidatul; Wirawan, Adi
Jurnal ILMU DASAR Vol 23 No 1 (2022)
Publisher : Fakultas Matematika dan Ilmu Pengetahuan Alam Universitas Jember

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.19184/jid.v23i1.23894

Abstract

Vibration testing on telemetry system payload is needed to determine its resistance to vibration during operation. Vibration testing of telemetry system payloads requires a test fixture. Test fixture is used to transmit vibration from shaker to telemetry system payload. The payload of telemetry system to be tested is a tubular. The test fixture in this study was designed using SolidWorks software. The material used for manufacture of test fixture is aluminum. Aluminum material was chosen because it has good rigidity with a relatively light mass. Stiffness and mass properties affect to natural frequency value of test fixture, which must be greater than the frequency range of operating telemetry system. Data collection uses two accelerometers placed on test fixture. Sine sweep vibrations are given from 5 Hz to 2000 Hz with a constant amplitude of 1 g and a sweep rate of 1 octave/minute. The test produces three peaks that they are candidates as natural frequencies, i.e at a frequency of 1532 Hz with an amplitude of 2.898 g, a frequency of 1706 Hz with an amplitude of 6.582 g, and at a frequency of 1806 Hz with an amplitude of 6.472 g. From those three natural frequencies, the second natural frequency at 1706 Hz is the most critically because it has the largest response value.
Persyaratan Kendali Terbang untuk Pesawat Terbang tak Berawak Sayap Tetap Suseno, Prasetyo Ardi Probo; Rizaldi, Ardian; Septiyana, Angga; Wijaya, Yusuf Giri; Pranoto, Fuad Surastyo
WARTA ARDHIA Vol. 48 No. 2 (2022)
Publisher : Sekretariat Badan Kebijakan Transportasi, Kementerian Perhubungan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.25104/wa.v48i2.470.12-22

Abstract

Dalam perancangan sistem kendali terbang dibutuhkan kriteria-kriteria khusus yang unik dari setiap pesawat untuk memenuhi spesifikasi misi yang diberikan dan untuk memenuhi kebutuhan stakeholder. Seperti halnya persyaratan perancangan pesawat, secara umum persyaratan desain sistem kendali diturunkan dari misi pesawat tersebut. Persyaratan tersebut juga harus memenuhi kontrak, standar, spesifikasi dan dokumen formal lainnya yang dikenakan dari para stakeholder. Setiap persyaratan desain kendali terbang tersebut harus dapat dibuktikan untuk memenuhi sertifikasi. Secara umum di Indonesia belum ada regulasi yang secara spesifik mewajibkan kriteria khusus tentang kendali terbang untuk dipenuhi pada pesawat terbang tak berawak, akan tetapi terdapat beberapa regulasi dan dokumen-dokumen standar untuk pesawat berawak sebagai panduan untuk menyusun kriteria - kriteria sistem kendali terbang. Makalah ini merangkum dokumen tersebut dan memberikan panduan dalam menyusun persyaratan untuk sistem kendali terbang pesawat udara tak berawak sayap tetap. Berdasarkan kajian yang telah dilakukan, persyaratan kendali terbang pada suatu pesawat sangat dipengaruhi oleh bentuk geometri dan inersia. Oleh karena sistem kendali terbang merupakan sistem berbasis software maka standar untuk sistem pesawat berbasis perangkat lunak juga harus diterapkan. Makalah ini juga memberikan metode verifikasi untuk sistem yang dirancang terhadap persyaratan yang telah disusun. Diharapkan makalah ini dapat dijadikan acuan bagi para desainer pesawat tak berawak untuk menyusun persyaratan untuk sistem kendali terbang yang dirancang.
Automatic Gain Control for UAV Stability Augmented System Using Jacobian Method Suseno, Prasetyo Ardi Probo; Rizaldi, Ardian; Wijaya, Yusuf Giri; Septiyana, Angga; Pranoto, Fuad Surastyo
Indonesian Journal of Aerospace Vol. 21 No. 1 (2023): Indonesian Journal of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.304

Abstract

A flight control system is an important system in aircraft to direct the aircraft and maintain the aircraft’s attitudes. One of the most important parts of the flight system is the stability augmented system designed to improve the stability of the aircraft during flight. This system is usually located as the most inner-loop part of the flight control system. There are many methods to design gain control feedback for aircraft stability systems. In this paper, the longitudinal stability augmented system for Unmanned Aerial Vehicle Albatross is designed using the Jacobian methods. The Jacobian method is capable to generate feedback value automatically within the limitation given by design requirements and objectives. This method allows a faster design for the stability augmented system on multi-trim points compared to the classical method such as PID tuning. The results that the designed system works well and conforms with the design requirements and objectives.
Design and experimental Verification of Vibration Testing Fixture for Flight Control Panel Wijaya, Yusuf Giri; Ula, Nur Mufidatul; P.P., Mikhael Gilang Pribadi; Muksin, Muksin; Syah, Agus Harno Nurdin
Indonesian Journal of Aerospace Vol. 19 No. 2 (2021)
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3701

Abstract

In this research, experimental design and testing of the vibration test fixture were carried out. The designed vibration test fixture is used to test the FCP, which is one of the components of avionics in aircraft. FCP vibration testing is carried out using the DO-160 test standard. The test has a test frequency range from 5 to 500 Hz. Therefore, the vibration test fixture must have a natural frequency above 600 Hz. The vibration test fixture is designed using a T-type model with modifications to get optimal results. The raw material used to make the test fixture is aluminum. The test fixture has a natural frequency value above 500 Hz, and both were tested using FEM simulation and experimental tests. Therefore, the vibration test fixture that is made meets the requirements for vibration testing on FCP. The difference in the natural frequency value from the FEM simulation and experimental test results on the vibration test fixture is 14.61% on the Z-axis, 10.61% on the X-axis, and 9.74 on the Y-axis.
COMPARATIVE STUDY OF WING LIFT DISTRIBUTION ANALYSIS USING NUMERICAL METHOD Septiyana, Angga; Hidayat, Kurnia; Rizaldi, Ardian; Wijaya, Yusuf Giri
Indonesian Journal of Aerospace Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3349

Abstract

This research focuses on calculating the force distribution on the wings of the LSU 05-NG aircraft by several numerical methods. Analysis of the force distribution on the wing is important because the wing has a very important role in producing sufficient lift for the aircraft. The numerical methods used to calculate the lift force distribution on the wings are Computational Flow Dynamics (CFD), Lifting Line Theory, Vortex Lattice Method and 3D Panel Method. The numerical methods used will be compared with each other to determine the accuracy and time required to calculate wing lift distribution. Because CFDs produce more accurate estimates, CFD is used as the main comparison for the other three numerical methods. Based on calculations performed, 3D Panel Method has an accuracy that is close to CFD with a shorter time. 3D Panel Method requires 400 while CFD 1210 seconds with results that are not much different. While LLT and VLM have poor accuracy, however, shorter time is needed. Therefore to analyze the distribution of lift force on the wing it is enough to use the 3D Panel Method due to accurate results and shorter computing time.
DESIGN OF FORCE MEASURING SYSTEM ON MAIN LANDING GEAR WEIGHT DROP TESTING MACHINE FOR THE APPLICATION OF LSU SERIES Wijaya, Yusuf Giri; Nurrohmad , Abian
Indonesian Journal of Aerospace Vol. 18 No. 2 Desember (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3377

Abstract

In this research, the design of the force measuring system on main landing gear weight drop test for the LSU series that developed by LAPAN was carried out. The principle of this machine is to apply the load according to the weight of the aircraft on the main landing gear and drop it at a certain height assisted by the guiding rail. At the bottom of this machine there is a impact platform where each angle is mounted with a load cell that functions to measure the reaction force due to the impact of the main landing gear. In addition, there is a data acquisition system whose function is to process the output signal from load cell and display measurement data. The data acquisition system used consists of DAQ measurement hardware made by national instruments and LabVIEW software installed on a PC. The design of this testing tools aims to carry out a dynamic impact test on the main landing gear structure of the UAV. In this study, static calibration has also been successfully performed on the impact platform and shows consistent results for various test masses.
Frequency Mapping of Square Head Expander for Vibration Testing Pratama, Mikhael Gilang Pribadi Putra; Muksin, Muksin; Wijaya, Yusuf Giri; Syah, Agus Harno Nurdin
Indonesian Journal of Aerospace Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3709

Abstract

Head expander is a component of an electro-dynamic shaker used for vibration tests in the vertical direction for large-size specimens. This study aims to determine the natural frequency distribution of the head expander across a certain number of predetermined points. This distribution map needs to be known to determine the better placement of future specimens on the head expander. In this study, the determination of natural frequency distribution is done through harmonic analysis (simulation) and experiment to form a contrast between the head expander's ideal condition and the actual condition. The frequency range in the middle of the Head Expander has almost the same value for both data types at 1550-1650 Hz. These results recommend that the best sample placement is in the middle of the Head Expander. The difference between the experimental and simulation low points has a not too far difference, which is 62.5 Hz. In contrast, at the highest value, the two have a quite far difference, which is 180.27 Hz. this difference can be caused by the improper installation of sensors on the Head Expander at certain points.
Co-Authors Adi Wirawan Hidayat, Kurnia Muksin, M. Nugroho, Yudha Agung Nurrohmad , Abian P.P., Mikhael Gilang Pribadi Pranoto, Fuad Surastyo Pratama, Mikhael Gilang Pribadi P. Pratama, Mikhael Gilang Pribadi Putra Pratama, Mukhael Gilang Pribadi Putra Rizaldi, Ardian Septiyana, Angga Suseno, Prasetyo Ardi Probo Syah, Agus Harno Nurdin Ula, Nur Mufidatul