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All Journal Bulletin of Electrical Engineering and Informatics Jurnal Aplikasi Bisnis dan Manajemen (JABM) E-Journal Jurnal RESTI (Rekayasa Sistem dan Teknologi Informasi) SINERGI: Jurnal Ilmiah Ilmu Manajemen Jurnal Pertahanan : Media Informasi tentang Kajian dan Strategi Pertahanan yang Mengedepankan Identity, Nasionalism dan Integrity JURNAL EDUCATION AND DEVELOPMENT NUSANTARA : Jurnal Ilmu Pengetahuan Sosial Jurnal Riset Informatika Jurnal Teknologi Dirgantara INSIST (International Series on Interdisciplinary Research) Journal of Robotics and Control (JRC) Budapest International Research and Critics Institute-Journal (BIRCI-Journal): Humanities and Social Sciences Journal of Strategic and Global Studies Jurnal Multidisiplin Madani (MUDIMA) Journal Research of Social Science, Economics, and Management Indonesian Journal of Community Services Indonesian Journal of Aerospace
Bura, Romie O.
Universitas Pertahanan Republik Indonesia
Religion Aerospace Engineering Agriculture, Biological Sciences & Forestry Arts Humanities Astronomy Chemical Engineering, Chemistry & Bioengineering Civil Engineering, Building, Construction & Architecture Computer Science & IT Control & Systems Engineering Decision Sciences, Operations Research & Management Economics, Econometrics & Finance Education Electrical & Electronics Engineering Engineering Environmental Science Industrial & Manufacturing Engineering Languange, Linguistic, Communication & Media Law, Crime, Criminology & Criminal Justice Library & Information Science Mechanical Engineering Medicine & Pharmacology Physics Social Sciences Other

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Implementing trajectory correction strategy through model prediction control for flight vehicle missions Irwanto, Herma Yudhi; Yusgiantoro, Purnomo; Abidin Sahabuddin, Zainal; Oktovianus Bura, Romie; Andiarti, Rika; Eko Putro, Idris; Sudiana, Oka; Hanif, Azizul
Bulletin of Electrical Engineering and Informatics Vol 13, No 5: October 2024
Publisher : Institute of Advanced Engineering and Science

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.11591/eei.v13i5.7798

Abstract

Modeling a high-speed flying vehicle is imperative to ensure the success of vehicle development missions. Moreover, adherence to research protocols mandates a stepwise approach to testing the vehicle model, encompassing simulation trials using software-in-the-loop simulation (SILS), hardware-in-the-loop simulation (HILS), as well as diverse ground and environmental tests prior to flight testing. This study entailed a collaborative effort between MATLAB/Simulink and LabVIEW to seamlessly integrate the model developed in MATLAB/Simulink into LabVIEW for the implementation of model predictive control (MPC) strategy, aimed at trajectory correction (TC) missions for the vehicle. This MPC strategy was directly applied to the onboard flight control system (OBFCS) of the vehicle. Simulation results indicate the successful control of roll and pitch conditions by OBFCS in both SILS and HILS, ensuring the maintenance of flight conditions in accordance with predicted trajectories despite the presence of simulated disturbances. Notably, the simulation demonstrates the independence or absence of interference between each simultaneous MPC control for roll and pitch adjustments.
Design of Inward-Turning External Compression Supersonic Inlet for Supersonic Transport Aircraft Utomo, Muhammad Adnan; Bura, Romie Oktavianus
International Series on Interdisciplinary Science and Technology Vol. 2 No. 2 (2017)
Publisher : Universitas Lampung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.23960/ins.v2i2.90

Abstract

Inward-turning external compression intake is one of the hybrid intakes that employs both external and internal compression intakes principle. This intake is commonly developed for hypersonic flight due to its efficiency and utilizing fewer shockwaves that generate heat. Since this intake employ less shockwaves, this design can be applied for low supersonic (Mach 1.4 - 2.5) intakes to reduce noise generated from the shockwaves while maintaining the efficiency. Other than developing the design method, a tool is written in MATLAB language to generate the intake shape automatically based on the desired design requirement. To investigate the intake design tool code and the performance of the generated intake shape, some CFD simulation were performed. The intake design tool code can be validated by comparing the shockwave location and the air properties in every intake's stations. The performance parameters that being observed are the intake efficiency, flow distortion level at the engine face, and the noise level generated by the shockwaves. The design tool written in MATLAB is working as intended. Two dimensional axisymmetric CFD simulations validation has been done and the design meets the minimum requirement. As for the 3D inlet geometry, with a little modification on diffuser and equipping vent to release the buildup pressure, the inlet has been successfully met the military standard on inlet performance (MIL-E-5007D). This design method also has feature to fit every possible throat cross sectional shapes and has been proven to work as designed.Keywords— Inward-turning, Supersonic, Engine Intakes, Low- noise, Design Method
Development of Optimization Methodology for Short Range Air-to-Air Missile Bura, Romie Oktovianus; Utama, Yudki; Farraz, Muhammad
International Series on Interdisciplinary Science and Technology Vol. 3 No. 1 (2018)
Publisher : Universitas Lampung

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.23960/ins.v3i1.111

Abstract

This paper illustrates the development and the use of conceptual sizing tools integrated with optimization tools. The conceptual sizing tool is based on empirical and simple analytical calculation that simple and robust enough for wide range of inputs. The genetic algorithm optimization method then used to explore the global optimum for given variables. System response analysis is conducted to gain insight about the sensitivity of objective function because of design variables.
Indonesia Military Research and Development in Dealing with the Sixth Generation Warfare: The Use of Artificial Intelligence in War Operations Irvan Arianto Randa Lembang; Romie Oktavianus Bura; R Djoko Andreas Navalino; Lutfi Adin Affandi
Jurnal Multidisiplin Madani Vol. 3 No. 5 (2023): May, 2023
Publisher : PT FORMOSA CENDEKIA GLOBAL

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55927/mudima.v3i5.3152

Abstract

Technological advancement has forced the international community to deal with the sixth generation of war, which is a conflict involving the most advanced robotics, artificial intelligence (AI), and satellite technology. This shows that warfare has evolved beyond traditional tactics because parties are no longer required to engage in face-to-face combat as they did during the first generation of conflicts. Although the "classic" war still takes place in some regions of the world, it is more sectoral in nature and only in small-scale wars. The researcher needed a description of Indonesian military research and development in dealing with sixth generation warfare: the application of artificial intelligence in military operations, hence the qualitative descriptive research approach was used. The Indonesian National Armed Forces (TNI) must be flexible in light of the dynamics of the world's swift technology advancements, which includes updating defense equipment with artificial intelligence (AI) functionality. Due to increasingly sophisticated danger patterns, the TNI must deploy artificial intelligence, making technological advancements crucial to safeguarding the security of border areas. Keeping the Republic of Indonesia's unitary state intact comes with a "fixed price," one of which is preserving the security of the border region
Aerodynamic Characteristic Optimization on The Design of Anti - Ship Missile for Indonesian Fast - Attack Boat Dwiastuty, Fuji; Bura, Romie Oktovianus; Triharjanto, Robertus Heru
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.a3157

Abstract

Missile is one of Indonesia 7 self – reliant main weapon system programs. Therefore research on the anti – surface ship missile system concept had been carried out at the Faculty of Defense Technology, Defense University. This research aims to abtain optimal design of anti – ship missile concept from previous research, i.e. 2 stages cruise missile with diameter of 0.36 m, total length of 5.19 m, cruise flight altitude of 17 m, and cruise flight speed of 0.88 Mach. The optimation is done on the missile’s aerodynamics characteristics to maximize its lift to drag ratio, which is one of the factor that determine the missile’s performance. Variables of nose cone shapes, number of wings, and body cross sections were chosen for evaluation of lift to drag ratio. The research found that nose cone shape did not affect the aerodynamic characteristics since the flight speed is subsonic. From the rest of the variables, it is found that the best configuration is missile with 2 wings with root length of 1.18 m, height of 0.79 m, and tip length of 0.71 m, elliptical body cross section, and the missile is to be flown at 6o angle of attack.
Numerical Investigation of Supersonic and Hypersonic Shock-Wave/Boundary-Layer Interactions Bura, Romie Oktovianus; Graham T. Roberts; Yufeng Yao; Neil D. Sandham
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.2025.12201

Abstract

Numerical simulations of 2-D supersonic and hypersonic laminar Shock-Wave/Boundary-Layer Interactions (SBLIs) were carried out by solving the Navier-Stokes (NS)equations using a compressible flow code over a wide range of Mach numbers and shockstrengths. The results obtained at Mach 2.0 and 7.73 were compared with experimentaldata. In addition, the numerical data were further analyzed using correlation laws derivedby previous researchers based on the free interaction concept, extended here to higherMach numbers. The results indicate that this concept is valid for separated laminar hypersonicflows with SBLIs. For interference heating, the correlation technique based on thewell-established power law relationship between peak heating and peak pressures yieldedencouraging results consistent with other correlations for laminar interference heating athypersonic speeds.
PERANCANGAN DAN ANALISIS INTEGRASI HYPERSONIC WAVERIDER–INLET SCRAMJET (DESIGN AND ANALYSIS OF HYPERSONIC WAVERIDER– SCRAMJET INLET INTEGRATION) Malik, Deden Ridwan; Bura, Romie Oktovianus
Indonesian Journal of Aerospace Vol. 12 No. 1 Juni (2014): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Nowadays, several hypersonic vehicle designs have existed and waverider is one of them. Waverider has been introduced for more than 50 years yet only a few have been operated. This is due to several difficulties in design processes dan propulsion system integration. The present research was conducted by designing general wedgederived waverider and integrating it with scramjet inlet. The waverider design process is based on one-dimensional flowfield analysis, while the scramjet inlet integration is based on exergy analysis. Through this investigation, a design variable – Exergy Destruction Rate (EDR) - would be obtained to correlate the waverider design with the integration of scramjet inlet
CHARACTERIZATION OF SIZE AND SHAPE OF AMMONIUM PERCHLORATE PARTICLE FROM CHINA, SOUTH KOREA, AND INDONESIA AND THEIR INFLUENCES ON PROPERTIES OF PROPELLANT Hutauruk, Jones; Bura, Romie Oktovianus; Wibowo, Heri Budi
Indonesian Journal of Aerospace Vol. 18 No. 1 Juni (2020): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3346

Abstract

The aim of this study is to obtain characteristics of ammonium perchlorate particle that used in Rocket Technology Center (LAPAN). Characterization begin from the determination of particle size distribution with Particle Size Analyzer. The SEM is used to obtain information about the morphology of AP, furthermore, the results are reprocessed using ImageJ software to analyze the shape of AP particle, and the Surface area was obtained by using BET. Characteristic of AP such as particle size, shape, and surface area are important parameters because those are directly related to propellant combustion energy. Ammonium perchlorate was procured from China, South Korea, and Indonesia with a particle size of 200µm From this study, the particle size of APC200, APH200 and API200 was obtained, which are 265 µm, 236 µm, and 242 µm, with particle shape aggregate value of 0,68, 0,38 and 0,33, roundness of 0,57, 0,79,0,63, and surface area of 1,104 m2/g, 5,561 m2/g, and 2,972 m2/g.
DESAIN DAN PENGUJIAN INTAKE KONIKAL SISTEM PROPULSI RAMJET PADA KECEPATAN SUPERSONIK (DESIGN AND TEST OF CONICAL INTAKE OF RAMJET PROPULSION SYSTEM AT SUPERSONIC SPEED) Sofyan, Sofyan; Bura, Romie Oktovianus
Indonesian Journal of Aerospace Vol. 13 No. 1 Juni (2015): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Riset ini bertujuan untuk mendesain intake supersonik untuk aplikasi sistem propulsi ramjet. Desain intake ramjet sangat penting bagi proses pembakaran dalam ruang bakar mesin ramjet. Dalam desain intake konikal ini, kondisi Mach 2 dijadikan sebagai acuan, dengan kompresi eksternal. Penelitian ini juga menguji intake ramjet dalam terowongan angin supersonik. Desain dilakukan dengan menempatkan gelombang kejut pada bibir cowl intake untuk memperoleh pressure recovery yang tinggi dan gaya hambat serendah mungkin. Hasil desain analitik dibandingkan dengan hasil numerik pada berbagai kondisi intake – subkritikal, kritikal, dan superkritikal. Hasil numerik juga divalidasi dengan eksperimen model. Intake yang didesain memberi pressure recovery sebesar 0,93, namun hasil ini cukup berbeda dengan hasil eksperimental. Ini disebabkan karena efisiensi kompresi tidak diikutkan dalam proses desain.
Co-Authors - Sofyan A. Octavian Agus Bayu Utama Amarulla Octavian Amperiawan, Gita Andi Fathurrachman Batara Sulo Andiarti, Rika Arif Nur Hakim Artono, Endro Aziz Ikhsan Bachtiar Boshra Algandouz Dadang Gunawan Deden Ridwan Malik Dwiastuty, Fuji Dwicahyono, Taufik Eko Priamadi Eko Putro, Idris Emhamed Boras Faisa Lailiyul Mutho' Affifah Faishal Irfan Farraz, Muhammad Gamantyo Hendrantoro Graham T. Roberts Hakim, Arif Nur Hanif, Azizul Haryanto A.R, Timbul Henry Setyanto Heri Budi Wibowo Heri Yansyah Herma Yudhi Irwanto Hutauruk, Jones Irdam Ahmad Irvan Arianto Randa Lembang Irwanto, Herma Yudhi Jamal Elbakay Elbakay Larasmoyo Nugroho Lilis Mariani, Lilis Luhut Simbolon Luky Adrianto Lutfi Adin Affandi Malik, Deden Ridwan Marimin , Martharaharja, Januar Arief Maspin Apit Mirad Fahri Muhammad Adnan Utomo Muhammad Farraz Muhammad Hanifudin Al Fadli Neil D. Sandham Octavian, A. Oka Sudiana Pujo Widodo, Pujo R Djoko Andreas Navalino Raden Andhika Ajiesastra Ratno Nuryadi Riska Nurtantyo Sarbini Salwa Muftah Eljamay Sarjito, Aris Shahed Muftah Shahrazad Eteer Siswo Hadi Sumantri Sofyan Sofyan Sovian Aritonang Sudiana, Oka Timbul Haryanto AR Triharjanto, Robertus Heru Utama, Yudki Utomo, Muhammad Adnan Wisnu Ari Adi Yudki Utama Yufeng Yao Yusgiantoro, Purnomo Zainal Abidin Sahabuddin, Zainal Abidin