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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) ASEAN Journal of Community Engagement Budapest International Research and Critics Institute-Journal (BIRCI-Journal): Humanities and Social Sciences Journal of Strategic and Global Studies Journal Research of Social Science, Economics, and Management Indonesian Journal of Community Services
Bura, Romie O.
Universitas Pertahanan Republik Indonesia
Religion Aerospace Engineering Agriculture, Biological Sciences & Forestry Arts Humanities Chemical Engineering, Chemistry & Bioengineering Computer Science & IT Control & Systems Engineering Decision Sciences, Operations Research & Management Economics, Econometrics & Finance Education Electrical & Electronics Engineering Engineering Environmental Science Languange, Linguistic, Communication & Media Law, Crime, Criminology & Criminal Justice Library & Information Science Mechanical Engineering Medicine & Pharmacology Physics Public Health Social Sciences Other

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Model Predictive Control in Hardware in the Loop Simulation for the OnBoard Attitude Determination Control System Irwanto, Herma Yudhi; Yusgiantoro, Purnomo; Sahabuddin, Zainal Abidin; Bura, Romie O.; Artono, Endro; Hakim, Arif Nur; Nuryadi, Ratno; Andiarti, Rika; Mariani, Lilis
Journal of Robotics and Control (JRC) Vol 5, No 2 (2024)
Publisher : Universitas Muhammadiyah Yogyakarta

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.18196/jrc.v5i2.21613

Abstract

Rocket flight tests invariably serve a purpose, one of which involves area monitoring or aerial photography. Consequently, the rocket necessitates the installation of a camera that remains consistently oriented toward the Earth's surface throughout its trajectory. Thus, ensuring the rocket's stability and preventing any rotation becomes imperative. To achieve this, the Onboard Attitude Determination Control System (OADCS) was researched and developed, fully controlled by NI myRIO with Labview as the programming language, ensures the rocket's attitude control and maintains a rolling angle of 0 degrees during flight. The MyRIO oversees the retrieval of attitude and position data from the X-Plane flight simulator, offering feedback through actuator control. The development of the OADCS proceeded incrementally through stages utilizing the Software in the Loop Simulation (SILS) and Hardware in the Loop Simulation (HILS) techniques, to ensure the verification of the system's functionality before its application to the rocket for real flight testing. In the OADCS control scheme, Model Predictive Control (MPC) is chosen, and it is compared with a PID controller to serve as a benchmark for processing speed. Because the rocket's flight time is short and its speeds of up to Mach 4. The simulation results indicate that MPC can halt the rocket's rotation 12 times more rapidly than PID control. Additionally, the MPC's ability to maintain a zero-degree rotation can persist throughout the rocket's flight time. Employing SILS and HILS enhances the OADCS rocket development process by incorporating MPC, which holds promise for application in real rockets.
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.
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 Dwicahyono, Taufik Eko Priamadi Eko Putro, Idris Emhamed Boras Faisa Lailiyul Mutho' Affifah Faishal Irfan Farraz, Muhammad Gamantyo Hendrantoro Hakim, Arif Nur Hanif, Azizul Haryanto A.R, Timbul Henry Setyanto Heri Yansyah Herma Yudhi Irwanto Irdam Ahmad Irwanto, Herma Yudhi Jamal Elbakay Elbakay Larasmoyo Nugroho Lilis Mariani, Lilis Luhut Simbolon Luky Adrianto Marimin , Martharaharja, Januar Arief Maspin Apit Mirad Fahri Muhammad Adnan Utomo Muhammad Farraz Muhammad Hanifudin Al Fadli Octavian, A. Oka Sudiana Pujo Widodo, Pujo Raden Andhika Ajiesastra Ratno Nuryadi Riska Nurtantyo Sarbini Salwa Muftah Eljamay Sarjito, Aris Shahed Muftah Shahrazad Eteer Siswo Hadi Sumantri Sovian Aritonang Sudiana, Oka Timbul Haryanto AR Utama, Yudki Utomo, Muhammad Adnan Wisnu Ari Adi Yudki Utama Yusgiantoro, Purnomo Zainal Abidin Sahabuddin, Zainal Abidin