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All Journal Warta Ardhia : Jurnal Perhubungan Udara Indonesian Journal of Aerospace
Septiyana, Angga
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Aerospace Engineering Astronomy Transportation

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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.
Pemilihan Airfoil Pesawat Terbang Tanpa Awak LSU-05 NG dengan Menggunakan Analytical Hierarchy Process Hidayat, Kurnia; Rizaldi, Ardian; Septiyana, Angga; Ramadiansyah, M. Luthfi; Ramadhan , Redha Akbar; Suseno, Prasetyo Ardi Probo; Jayanti, Eries Bagita; Atmasari, Novita; Nurtiasto , Taufiq Satrio
Indonesian Journal of Aerospace Vol. 17 No. 2 Desember (2019): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a3161

Abstract

Pada perancangan pesawat terbang tanpa awak, pemilihan airfoil sangat penting untuk meningkatkan performa pesawat. Airfoil dipilih berdasarkan karakteristik geometri dan performa aerodinamikanya. Penelitian ini membahas tentang pemilihan airfoil dengan banyak kriteria berdasarkan karakteristik masing-masing airfoil. Pada tahap awal, sebanyak 1504 airfoil tersaring menjadi 5 airfoil terpilih. Airfoil tersebut dianalisis berdasarkan 7 kriteria utama, yaitu Camber, Thickness, Manufacturability, Max C_L, C_(L_0 ), Max C_L angle, dan Max L/D. Berdasarkan analisis tersebut, FX 76-MP-160 terpilih sebagai airfoil terbaik untuk pesawat terbang tanpa awak yang dirancang.
STABILITY AND CONTROLABILITY ANALYSIS ON LINEARIZED DYNAMIC SYSTEM EQUATION OF MOTION OF LSU 05-NG USING KALMAN RANK CONDITION METHOD Septiyana, Angga; Hidayat, Kurnia; Rizaldi, Ardian; Suseno, Prasetyo Ardi Probo; Jayanti, Eries Bagita; Atmasari, Novita; Ramadiansyah, M. Luthfi; Ramadhan, Redha Akbar
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.a3318

Abstract

This paper discusses the stability, control and observation of the dynamic system of the Lapan Surveillance UAV 05-NG (LSU 05-NG) aircraft equation. This analysis is important to determine the performance of aircraft when carrying out missions such as photography, surveillance, observation and as a scientific platform to test communication based on satellite. Before analyzing the dynamic system, first arranged equations of motion of the plane which includes the force equation, moment equation and kinematics equation. The equation of motion of the aircraft obtained by the equation of motion of the longitudinal and lateral directional dimensions. Each of these equations of motion will be linearized to obtain state space conditions. In this state space, A, B and C is linear matrices will be obtained in the time domain. The results of the analysis of matrices A, B and C show that the dynamic system in the LSU 05-NG motion equation is a stable system on the longitudinal dimension but on the lateral dimension directional on the unstable spiral mode. As for the analysis of the control of both the longitudinal and lateral directional dimensions, the results show that the system is controlled.
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.
Co-Authors Atmasari, Novita Hidayat, Kurnia Jayanti, Eries Bagita Nurtiasto , Taufiq Satrio Pranoto, Fuad Surastyo Ramadhan , Redha Akbar Ramadhan, Redha Akbar Ramadiansyah, M. Luthfi Rizaldi, Ardian Suseno, Prasetyo Ardi Probo Wijaya, Yusuf Giri