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All Journal 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 Warta Ardhia: Jurnal Transportasi
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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RANCANG BANGUN MICRO AIR VEHICLE KONFIGURASI TAILLESS Mulyanto, Taufiq; Wijaya, Arinta H; Muhammad, Hari
Mesin Vol 23, No 2 (2008)
Publisher : Mesin

Show Abstract | Download Original | Original Source | Check in Google Scholar | Full PDF (9480.792 KB)

Abstract

Nowadays, Micro Air Vehicle (MAV) is mostly developed for surveillance purpose, either for military or civilian. In this article, a design and building of a MAV will be presented. A tailless configuration was chosen. The design and build process started with a study of several design parameters of existing MAVs. Then, it is followed by initial sizing, detail design and production of the MAV. In general, the designed MAV could meet the design requirements and objectives stated. Some preliminary tests had shown that the basic flying characteristics was sufficiently good, although further development still has to be done. The design and build process was also able to evaluate the implementation of some aircraft design formula and method being implemented to design MAV.
RANCANG BANGUN MICRO AIR VEHICLE KONFIGURASI TAILLESS Taufiq Mulyanto; Arinta H Wijaya; Hari Muhammad
Mesin Vol. 23 No. 2 (2008)
Publisher : Mesin

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Abstract

Nowadays, Micro Air Vehicle (MAV) is mostly developed for surveillance purpose, either for military or civilian. In this article, a design and building of a MAV will be presented. A tailless configuration was chosen. The design and build process started with a study of several design parameters of existing MAVs. Then, it is followed by initial sizing, detail design and production of the MAV. In general, the designed MAV could meet the design requirements and objectives stated. Some preliminary tests had shown that the basic flying characteristics was sufficiently good, although further development still has to be done. The design and build process was also able to evaluate the implementation of some aircraft design formula and method being implemented to design MAV.
UJI AERODINAMIK MODEL KAPAL BERSAYAP WING IN SURFACE EFFECT SEBAGAI INPUT KAJIAN GERAK PLANNING MENJELANG TAKE-OFF - Iskendar; A. Farid Widodo; Taufiq Mulyanto; Paulus Indiyono
Jurnal Teknologi Dirgantara Vol. 8 No.1 Juni 2010
Publisher : National Institute of Aeronautics and Space - LAPAN

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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.
RANCANG BANGUN MODEL WAHANA HOVERWING XHW-1 Taufiq Mulyanto; Digit Mitra Baruna
Jurnal Teknologi Dirgantara Vol 9, No. 2 Desember (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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. Keywords: Hoverwing, Hovercraft, WiSE-craft, Design, Model build
Conceptual Design of a 10-Seater Electric Aircraft A Marcell; Frentsen Limor; J F Humairah; M D T Z Baniz; Taufiq Mulyanto
AVIA Vol 4, No 1: (June, 2022)
Publisher : Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v4i1.57

Abstract

With the increase in population, an increase of transportation needs is inevitable, especially in air travel. There is an underlying problem in this matter that is carbon pollutions. Air travel contributes around 2% of the global emissions. This paper contains the conceptual design of 10-seater electric aircraft that can serve as a cleaner alternative for air travel. The paper will discuss about our objectives and the results of configurations, backed with calculations of proof in all aspects that is needed. In conclusions, this paper presents a conceptual design of 10-seater electric aircraft that have range more than 450 km. The aircraft being designed has a mid-wing three surface configuration with a MTOW of 7250 kg.
Conceptual Design of a 10-Seater Electric Aircraft Marcell, A; Limor, F; Humairah, J F; Baniz, M D T Z; Mulyanto, Taufiq
International Journal of Aviation Science and Engineering - AVIA Vol. 5 No. 2: (December,2023)
Publisher : FTMD Institut Teknologi Bandung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/avia.v5i2.94

Abstract

With the increase in population, an increase of transportation needs is inevitable, especially in air travel. There is an underlying problem in this matter that is carbon pollutions. Air travel contributes around 2% of the global emissions. This paper contains the conceptual design of 10- seater electric aircraft that can serve as a cleaner alternative for air travel. The paper will discuss about our objectives and the results of configurations, backed with calculations of proof in all aspects that is needed. In conclusions, this paper presents a conceptual design of 10-seater electric aircraft that have range more than 450 km. The aircraft being designed has a mid-wing three surface configuration with a MTOW of 7250 kg
Design and Analysis of a Ten-Passenger Electric Aircraft Named Djinn Mulyanto, Taufiq; K Musyahada; F Carakapurwa; F Jatmiko; C Puspaningtyas; F Hanafi; Huda, Zulmiftah; Hamdani, Fadil
Journal of Applied Science, Engineering and Technology Vol. 4 No. 2 (2024): December 2024
Publisher : INSTEP Network

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.47355/jaset.v4i2.72

Abstract

As aircraft industries contribute more than 12% of the carbon emission globally, the urgency to develop a more sustainable and reliable source of energy to power aircrafts has become greater. Regarding that concern, an electric-powered aircraft is proposed to become the solution for the search of green technology. An electric aircraft has been proven to be capable of reducing carbon emission and sound emission. Despite of the advantages, the use of electric aircraft is still very scarce since there are a lot of considerable issues such as low energy density power sources, reliability problems, and the lack of design references. As a contribution for the development process, an electric aircraft by the name of “Djinn” has been designed, in hope that this aircraft can be an addition to the references for future endeavors. The methods used for designing the aircraft is similar as the methods used for developing conventional aircrafts, with slightly modified approximation and assumptions.
Cabin Fire Risks of Hydrogen-Powered Aircraft: Comparative Analysis and Safety Implications Nugraha, Wahyu Cakra; Mulyanto, Taufiq; Petit, Jean-François; Jézégou, Joël
Langit Biru: Jurnal Ilmiah Aviasi Vol 18 No 2 (2025): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.54147/langitbiru.v18i2.1115

Abstract

Liquid hydrogen (LH2) is being developed as an alternative aircraft fuel to support the decarbonisation of aviation. Although free of carbon emissions upon combustion, LH2 poses safety challenges, particularly in the confined environment of aircraft cabins. This study aims to identify potential fire hazards due to leakage and use of LH2 through a literature-based comparative analysis of kerosene. The study results show that LH2 has a wide flammability range, low ignition energy, and almost invisible flame, making early detection difficult. Cryogenic properties, explosive potential (BLEVE) and rapid gas dispersion also add to the risk. Therefore, the integration of LH2 in aircraft requires specialised detection systems, adequate cabin ventilation design and updated safety standards to suit the unique characteristics of liquid hydrogen.
Certification Process of Starlink Wifi on A320 Aircraft Malau, Roni Hasudungan; Mulyanto, Taufiq; Imam Nurhakim, Muhamad Luthfi
Langit Biru: Jurnal Ilmiah Aviasi Vol 18 No 1 (2025): Langit Biru: Jurnal Ilmiah Aviasi
Publisher : Politeknik Penerbangan Indonesia Curug

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.54147/langitbiru.v18i1.1290

Abstract

Driven by the growing demand for seamless in-flight internet access and efforts to enhance passenger comfort, airlines are increasingly adopting in-flight connectivity technologies such as the Starlink Wi-Fi system. Integrating these systems into aircraft requires obtaining Supplemental Type Certificate (STC) approval from aviation authorities to ensure compliance with airworthiness standards. This paper examines the certification process for installing Starlink Wi-Fi on A320 aircraft under EASA and DGCA regulations, with a focus on airworthiness aspects. The process involves defining the design description, classifying the modification, and identifying the certification basis and compliance requirements. The installation is classified as a non-significant major change under both regulatory frameworks, requiring adherence to specific certification basis, Means of Compliance, and Design Organization Approval (DOA) frameworks. DGCA mandates Class C and D DOA, while EASA employs a single DOA structure based on approved privileges, highlighting distinct regulatory approaches to certification.
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.
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 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, Rianto Adhy susilo, bangkit Widadi, Novyanto Widodo, A. Farid Wijaya, Arinta H Y. H. Yogaswara, Y. H. Zulkarnain, Muhammad Fikri