Article Per Year (5 Year)
p-Index From 2020 - 2025
0.751
P-Index
This Author published in this journals
All Journal Jurnal Teknologi dan Sistem Komputer Jurnal Teknologi Dirgantara Journal of Petroleum and Geothermal Technology Pattimura Proceeding : Conference of Science and Technology
Singgih Satrio Wibowo
Department Of Mechanical Engineering, Politeknik Negeri Bandung
Aerospace Engineering Agriculture, Biological Sciences & Forestry Astronomy Biochemistry, Genetics & Molecular Biology Chemical Engineering, Chemistry & Bioengineering Chemistry Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Earth & Planetary Sciences Electrical & Electronics Engineering Energy Engineering Materials Science & Nanotechnology Mathematics Mechanical Engineering Physics

Published : 5 Documents Claim Missing Document
Claim Missing Document
Check
Articles

Found 5 Documents
Search

 1 
Pengaruh Masukan Kendali Terhadap Hasil Identifikasi Parameter Pesawat Udara Konfigurasi Konvensional Matra Terbang Longitudinal Eries Bagita Jayanti; Novita Atmasari; Hidayati Mardikasari; Ardian Rizaldi; Fuad Surastyo Pranoto; Singgih Satrio Wibowo
Jurnal Teknologi dan Sistem Komputer Volume 7, Issue 1, Year 2019 (January 2019)
Publisher : Department of Computer Engineering, Engineering Faculty, Universitas Diponegoro

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (441.737 KB) | DOI: 10.14710/jtsiskom.7.1.2019.25-30

Abstract

Parameter identification is a process to get real characteristics of the motion dynamics of an object which can then be used to build the dynamics model of the object, which has a very high level of validity and accuracy. The modeling process is usually carried out using aircraft input data and the results of existing navigation data recording. From the data, the model parameters are estimated using the simple least square method. In this study, the simulation was carried out by varying the deflection input in the control field and simulation time. The input given to the longitudinal dimension is the deflection of the elevator control field. The results of parameter identification in the Corsair A-7A plane in the longitudinal dimension indicate that the input form 3-2-1 has a smaller error value than using doublet and pulse inputs. This shows that the input form 3-2-1 is most suitable for the longitudinal dimension among the given inputs.
PERHITUNGAN FAILURE INDEX STRUKTUR SAYAP PESAWAT TERBANG TANPA AWAK Ai-X1 DENGAN MENGGUNAKAN KRITERIA TSAI-HILL DISIMULASIKAN DENGAN METODE ELEMEN HINGGA Lenny Iryani; Singgih Satrio Wibowo
Jurnal Teknologi Dirgantara Vol. 18 No.1 Juni 2020
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3228

Abstract

Untuk mengetahui kekuatan struktur suatu pesawat terbang, dilakukan perhitungan dan analisis kekuatan struktur. Struktur sayap pesawat terbang yang disusun dari material komposit, penghitungan dan analisis kekuatan struktur salah satunya dilakukan dengan menghitung failure index untuk masing-masing layer/susunan dari material komposit tersebut. Pada penelitian ini, struktur sayap Pesawat terbang tanpa awak (PTTA) Ai-X1 yang terbuat dari material komposit dianalisis kekuatan strukturnya dengan menghitung failure index dari masing-masing layer/susunan material komposit tersebut. Perhitungan failure index dilakukan dengan menggunakan kriteria kegagalan Tsai-Hill. Hasil dari penelitian ini yaitu nilai failure index pada masing-masing layer/susunan material komposit struktur sayap pesawat Ai-X1. Berdasarkan kriteria Tsai-Hill masing-masing layer/susunan tersebut menunjukkan tidak adanya keretakan pada lamina.
TERAPAN FUNGSI SIGMOID UNTUK MENENTUKAN NILAI MAKSIMAL KOEFISIEN GAYA ANGKAT DAN SUDUT STALL PADA KURVA LINEAR CL TERHADAP α Angga Septiyana; Singgih Satrio W; Fuad Surastyo P; Try Kusuma Wardana; Ardian Rizaldi; Novita Atmasari; Eries Bagita Jayanti; Prasetyo Ardi P
Pattimura Proceeding 2021: Prosiding KNM XX
Publisher : Pattimura University

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (1869.194 KB) | DOI: 10.30598/PattimuraSci.2021.KNMXX.327-334

Abstract

Karya tulis ilmiah ini membahas tentang terapan fungsi sigmoid untuk menentukan nilai maksimal gaya angkat dan sudut stall pada pesawat berdasarkan hasil simulasi dengan menggunakan perangkat lunak XFLR5.Nilai maksimal gaya angkat dan sudut stall pada sebuahpesawatmerupakankomponenyangharusdiketahuiagarpesawattidakmengalamistall. Dimana pada saat pesawat sudah mencapai sudut stall pesawat akan kehilangan gaya angkat dan menyebabkan pesawat jatuh. Perangkat lunak XFLR5 digunakan untuk mensimulasikan sertauntukmendapatkankurvakoefisiengayaangkat CLterhadapsudutserang α. Hasilsimulasi dengan menggunakan perangkat lunak XFLR5 menunjukkan grafik CL terhadap α bersifat linear yang artinya tidak dapat diketahui dimana koefisien gaya angkat maksimal dan sudut serang dimana pesawat mengalami stall. Hasil penelitian ini fungsi sigmoid ini dapat diterapkan untuk menentukan nilai maksimal koefisien gaya angkat dan sudut stall dari pesawat. Penelitian yang dilakukan dengan memilih nilai transition rate M sebesar 0.8 diperoleh hasilnilai koefisien gaya angkat maksimal 1.2648 dan sudut stall sebesar 13◦
Identification of Aircraft Parameters in the Lateral-Directional Flight Dimension with Variation of Control Input Eries Bagita Jayanti; Fuad Surastyo Pranoto; Singgih Satrio Wibowo
Jurnal Teknologi Dirgantara Vol 20, No 1 (2022)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3658

Abstract

In this research, the process of identifying aircraft parameters is carried out for the lateral-directional dimension by notice the variations of the given control surface deflection input. The inputs are pulse, doublet and 3-2-1-1. Among the input forms, it is not known which form is most suitable for the lateral-directional dimension. Simulation is done by varying the input deflection control surface and simulation time. The input given is deflection of the aileron and rudder control surfaces. This research uses the equation error method with the ordinary least square estimation technique. The purpose of this research to identify the most suitable input for the identification of parameters in the lateral-directional dimension and to observe the effect of simulation time. The aircraft used is the Lockheed C-5 Galaxy. The simulation results show that the combination of the 3-2-1-1 input form in the aileron deflection surface and the input pulse shape on the rudder has an error value of about 0.09. This value is smaller among all cases seen from the error matrix A. Based on that, the combination of the two inputs is the most suitable for the lateral-directional dimension than the other inputs that have been given.
Development of Torque and Drag Calculation Software for Oil Well Planning–Part 1: 2D Aadnoy Method Singgih Satrio Wibowo; Herman Yoseph Sutarto
Journal of Petroleum and Geothermal Technology Vol 3, No 2 (2022): November
Publisher : Universitas Pembangunan Nasional "Veteran" Yogyakarta

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.31315/jpgt.v3i2.7503

Abstract

With the increasing number of drilled ultra-extended reach wells and complex geometry wells, the drilling limitation caused by excessive torque and drag forces must be further investigated. The wellbore friction being a main limiting factor in extended reach well needs to be studied with the new developed models. The torque and drag software implement two methods: (1) 2D and 3D analytical model developed by Aadnøy (Aadnoy & Andersen, 1998; Aadnoy & Andersen, 2001; Aadnoy & Djurhuus, 2008; Aadnoy, et al., 2010; Aadnoy, 2010) and (2) Miska and Mitchel, for 2D wellbore (Mitchell, et al., 2011). This paper presents the theory and implementation of 2D Aadnoy method. Quite diverse wellbore trajectory and depth has been chosen for a better evaluation and comparison of the model with the measured data. In order to investigate the potential and limitation of the model, torque and drag analysis during the different operations such as tripping in, tripping out, rotating off bottom, combined up/down were investigated.
Co-Authors Angga Septiyana Ardian Rizaldi Ardian Rizaldi Eries Bagita Jayanti Eries Bagita Jayanti Eries Bagita Jayanti Fuad Surastyo P Fuad Surastyo Pranoto Fuad Surastyo Pranoto Herman Yoseph Sutarto Hidayati Mardikasari Lenny Iryani Novita Atmasari Novita Atmasari Prasetyo Ardi P Try Kusuma Wardana