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All Journal Warta Ardhia : Jurnal Perhubungan Udara Mesin Jurnal Teknologi Dirgantara International Journal of Aviation Science and Engineering Langit Biru: Jurnal Ilmiah Aviasi Journal of Applied Science, Engineering and Technology (J. ASET) Indonesian Journal of Aerospace
Mulyanto, Taufiq
Kelompok Keilmuan Desain, Operasi Dan Perawatan Pesawat Terbang, Fakultas Teknik Mesin Dan Dirgantara, Institut Teknologi Bandung
Aerospace Engineering Astronomy Automotive Engineering Chemical Engineering, Chemistry & Bioengineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Decision Sciences, Operations Research & Management Education Electrical & Electronics Engineering Engineering Environmental Science Industrial & Manufacturing Engineering Mechanical Engineering Physics Transportation

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Analisis Topologi Jaringan Penerbangan Indonesia Menurut PM 88 Tahun 2013 Sembiring, Javensius; Fathurrohim, Luqman; Mulyanto, Taufiq; Yarlina, Lita; Widadi, Novyanto
WARTA ARDHIA Vol. 48 No. 1 (2022)
Publisher : Sekretariat Badan Kebijakan Transportasi, Kementerian Perhubungan

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.25104/wa.v48i1.445.15-24

Abstract

Penelitian ini memodelkan jaringan penerbangan domestik yang diatur dalam PM 88 Tahun 2013 dari sisi topologinya. Analisis topologi dilakukan baik dari sisi sistem jaringan sebagai satu jaringan yang terintegrasi dan analisis dari sisi peran bandara yang secara signifikan berpengaruh terhadap jaringan. Berdasarkan analisis jaringan sebagai sistem yang terintegrasi diperoleh bahwa satu bandara terkoneksi rata-rata dengan 7 bandara lainnya, rute terjauh dapat dijangkau dengan 6 kali penerbangan, jaringan mengikuti distribusi power-law, dua bandara rata-rata dapat ditempuh dengan 3 kali penerbangan. Sedangkan dari sisi peran bandara diperoleh bahwa bandara CGK, SUB, UPG, AMQ, MDC, DPS, BPN, dan KNO memiliki kontribusi yang sangat penting bagi jaringan domestik berjadwal seperti yang diatur dalam PM 88 Tahun 2013. Kontribusi per bandara ini dikuantifikasi melalui metrik seperti degree of centrality, betweenness centrality, eigenvector centrality, dan page rank.
PENGEMBANGAN SISTEM AILERON PESAWAT TERBANG BERBASIS ELEKTROMEKANIK susilo, bangkit; Suwondo, Edy; Mulyanto, Taufiq
Mesin Vol 30 No 1 (2024)
Publisher : Faculty of Mechanical and Aerospace Engineering

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.5614/MESIN.2024.30.1.2

Abstract

More Electric Aircraft (MEA) dan Zero Emission Aircraft (ZEA) adalah masa depan pengembangan pesawat terbang, hingga saat ini MEA dan ZEA belum mendapat sertifikasi tipe dari regulator kelaikan udara. Berdasarkan kondisi tersebut, pada penelitian ini akan dilakukan studi terkait penggunaan sistem elektromekanik pada  kendali aileron pesawat terbang. Penelitian ini  dimulai dengan memilih pesawat yang memenuhi regulasi Civil Aviation Safety Regulation (CASR) 23, yang kemudian sistem kendali aileron pesawat yang ada diganti dengan sistem berbasis elektromekanikal. Proses ini mencakup analisis kehandalan sistem menggunakan Fault Tree Analysis FTA. Kemudian analisis daya dan berat dilakukan untuk memastikan sistem yang baru dapat diterapkan. Pada akhir studi ini, didapatkan hasil analisis kegagalan sistem menunjukkan bahwa arsitektur  yang diusulkan memiliki tingkat kegagalan sekitar 9.324 × 10−8 pada kondisi loss of aileron control dan 1.09× 10−10  pada kondisi aileron hard over dan   hasil tersebut sudah memenuhi persyaratan regulasi. Analisis daya menunjukkan bahwa daya yang diperlukan hanya 1667,8 Watt, sehingga daya yang tersedia pada pesawat masih mencukupi. Namun, analisis berat menunjukkan bahwa sistem elektromekanikal yang baru lebih berat sekitar 35,7% dibandingkan sistem mekanikal yang digunakan sebelumnya.
Evaluation of Artificial Neural Networks Technique for Calibration of Five-Hole Probe Measurement Birry, Abdurrahman; Arifianto, Ony; Mulyanto, Taufiq
Indonesian Journal of Aerospace Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2024.2784

Abstract

In the present study, the Artificial Neural Networks (ANN) technique was implemented to predict the flow parameters of a Five-Hole Probe (FHP). The experimental data were obtained from a subsonic open jet wind tunnel at a speed increased from 0 to 1180 rpm in increments of 200 rpm. The ANN approach is carried out in stages, starting with the method of selecting training data and validation, then increasing the number of neurons, varying the correlation between the activation function and the optimizer, and finally finding the optimal number of hidden layers. In the ANN approach, the mean absolute errors of 0.2705, 0.3326, and 1.0748 were achieved for estimating angle α which represents the angle of attack, angle β which represents the angle of sideslip, and speed, respectively. At the end of this study, the results were compared with the rational function approach. It was concluded that the ANN approach was more accurate compared to the rational function based on statistical parameters such as mean absolute error, max absolute error, and coefficient of determination (r2).
Model-Based Systems Engineering Capabilities to Connect Descriptive and Analytic Model: Case Studies Hybrid Propulsion of Electric Aircraft Zulkarnain, Muhammad Fikri; Nurprasetio, Ignatius Pulung; Mulyanto, Taufiq; Pasaribu, Hisar Manongam
Indonesian Journal of Aerospace Vol. 22 No. 1 (2024): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2024.2787

Abstract

Model-based Systems Engineering (MBSE) is a system development framework that utilizes the formalization of modeling to support systems engineering processes beginning early in the system development stage. This research aim is to explore and evaluate the implementation of the MBSE tool chain, especially in descriptive-analytic capabilities, traceability, ease of design customizations, and ease of making changes. MBSE processes, including requirements definition, functional decomposition, physical decomposition (architecture), and analysis were performed using a case study. The case study is the design and analysis of several hybrid propulsion configurations for electric aircraft. The ease of change and modification is shown by the process of adding, removing, and rerouting system elements and connections to modify from one configuration to another. Analysis has been performed by modeling the analysis context via the SysML Block Diagram, the interconnection of value via the SysML Parametric Diagram, and the calculation and results via the Cameo Instance Table. The result of the proposed propulsion model in SysML for full electric configuration has similar results to reference, while the results for hybrid propulsion have similar trends compared to other studies without MBSE. The method to compare analysis results and requirements with Measure of Performances (MoPs) as mediators has been proposed and performed
Guidance and Control System Design of a Surface-to-Air Missile Based on 122 mm Rocket Yogaswara, Y. H.; Alvin Ardiansyah; Rianto Adhy Sasongko; Taufiq Mulyanto
Indonesian Journal of Aerospace Vol. 23 No. 1 (2025): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2025.9041

Abstract

This paper applies and analyzes the design of a proportional navigation guidanceand control system for a 122 mm rocket platform. The research involves modeling missiledynamics, guidance systems, and control systems. The missile dynamics model relies onthe 6 DOF (Degrees of Freedom) equation for a rigid body, with aerodynamic data obtainedfrom the Missile Datcom program. The propulsion model is generated by a genericthrust profile of a 122 mm unguided rocket. The guidance system model is based on theproportional navigation guidance law, and the control system model employs the LinearQuadratic Regulator (LQR) method. Modeling is conducted using Simulink software, andsimulations encompass various scenarios. The analysis considers aspects such as missiletrajectory, acceleration command, actual acceleration, control surface deflection, and thetime required to hit the target. The simulation results indicate the missile’s capability tointercept targets under numerous conditions, although limitations are observed in specifictarget scenarios where interception is not achievable.
RANCANG BANGUN MODEL WAHANA HOVERWING XHW-1 Mulyanto, Taufiq; Baruna, Digit Mitra
Indonesian Journal of Aerospace Vol. 9 No. 2 Desember (2011): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Hoverwing craft is a combination of hovercraft and WiSE-craft. Hoverwing craft operation has transition phase from air cushion lift to aerodynammic lift, and vice versa. A Hovering model, named XHW-1, was designed and built to understand further the design problem related to this kind of vehicle and to observe the transition phase. To simplify construction, manufacture and testing, but without reducing the uniqueness of the vehicle, the model was designed to be operated on a flat surface. The design considered hovercraft related aspect and aircraft aspect as well. The configuration chosen was monohull. The model weight 755 gr, has 1.2 m wing span, and 20 x 30 cm air cushion. Preliminary test showed that air cushion could function properly and that model could reach 3 m/s forward speed.
UJI AERODINAMIK MODEL KAPAL BERSAYAP WING IN SURFACE EFFECT SEBAGAI INPUT KAJIAN GERAK PLANNING MENJELANG TAKE-OFF Iskendar; Widodo, A. Farid; Mulyanto, Taufiq; Indiyono, Paulus
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper describes aerodynamic tests (wind tunnel tests) for a model of Wing in Surface Effect Craft 8 seater, WiSE-8. The tests were conducted at UPT-Laboratorium Aero Gasdinamika dan Getaran (LAGG)-BPPT, PUSPIPTEK, Serpong, to determine the performance of the lift and pre-take off craft conditions. This craft model with scale of 1 per 6 was tested with rigid body - upside up - power off method. The profile of craft wing model was aerofoil form, Clark-Y. The craft model test with complete configuration (Wing-Body-Pontoon-Nacelle-Tail) was carried out with the following parameters, wind speed of 20, 30, 40, and 50 m per sec, angle of attack of -6 to 18 degree, yaw angle of 0 degree, ground board height 0-1 m (in respect to prototype value of 0-6 m). Meanwhile,the tests of air flow visualization were carried out by using wool tuft at speed of 40 m per sec. The result of wind tunnel test consisting of CL, CD, CM, and CL-CD was validated by theoritical calculation using Vortex Lattice Method (VLM) and Datcom software. Then this result was evaluated and extrapolated to predict the movement of WiSE-8 in the pre take off performance condition, especially in the longitudinal direction.
Co-Authors - Iskendar A Marcell A. Farid Widodo Alvin Ardiansyah Arifianto, Ony Arinta H Wijaya Baniz, M D T Z Baruna, Digit Mitra Birry, Abdurrahman C Puspaningtyas Digit Mitra Baruna Edy Suwondo, Edy F Carakapurwa F Hanafi F Jatmiko Frentsen Limor Hamdani, Fadil Hari Muhammad Huda, Zulmiftah Humairah, J F Imam Nurhakim, Muhamad Luthfi Iskendar J F Humairah Javensius Sembiring Javensius Sembiring, Javensius Jézégou, Joël K Musyahada Limor, F Lita Yarlina Lita Yarlina, Lita Luqman Fathurrohim M D T Z Baniz Malau, Roni Hasudungan Marcell, A Novyanto Widadi Nugraha, Wahyu Cakra Nurprasetio, Ignatius Pulung Pasaribu, Hisar Manongam Paulus Indiyono Paulus Indiyono Petit, Jean-François Rianto Adhy Sasongko susilo, bangkit Widadi, Novyanto Widodo, A. Farid Wijaya, Arinta H Y. H. Yogaswara, Y. H. Zulkarnain, Muhammad Fikri