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Andri Agus Rahman
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INDONESIA
Indonesian Journal of Aerospace
Published by Badan Riset dan Inovasi Nasional
ISSN : -     EISSN : 30320895     DOI : https://doi.org/10.55981/ijoa
Core Subject : Science, Engineering,
Aerospace Engineering Astronomy
Indonesian Journal of Aerospace provides a broad opportunity for the scientific and engineering community to report research results, disseminate knowledge, and exchange ideas in various fields related to aerospace science, technology, and policy. Topics suitable for publication in the IJoA include (but are not limited to) Space science (astrophysics, heliophysics, magnetospheric physics, ionospheric physics, etc.), Aeronautics technology (dynamic, structure, mechanics, avionics, etc.), Space technology (rocket, satellite, payload system, control, etc.), Propulsion and energetic technology (propellant, rocket static-test, thermodynamics of propulsion system, etc.), Aeronautics and space policy, and Application of aerospace science and technology.
Arjuna Subject : Ilmu Bumi dan Planet (semua kategori) - Ruang Angkasa dan Ilmu Planet
Articles 364 Documents
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Impact of Airfoil Section on Winglet Design for Enhancing Aerodynamics Performance of Aircraft using CFD Analysis Pinindriya, Sinung Tirtha; Soemaryanto, Arifin Rasyadi; Fajar, Muhammad; Hidayat, Kurnia; Hamonangan, Jefri Abner; Ramadiansyah, Mohamad Luthfi
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.900

Abstract

This research paper investigates the influence of airfoil section on winglet design to enhance aerodynamic performance while considering structural aspects. The selection of the airfoil section significantly affects the distribution of lift and drag along the winglet, influencing the overall lift-to-drag ratio of the aircraft and its ability to reduce drag by smoothing the airflow over the wingtip. Three airfoil sections, namely NACA 0010 (symmetrical), NACA 64-009 (thin cambered), and PSU 94-047 (cambered), were compared using computational fluid dynamics (CFD) simulations. The study examines the forces and moments experienced by the winglet, including drag force, lift force, and bending moment on wing surface. The CFD simulations were conducted using a Computational Wind Tunnel (CWT) tool, which employs numerical methods and mathematical models to analyze fluid flow around objects. The solver code is based on RANS method. The wind tunnel testing is provided to validate one of CFD simulation results. The findings indicate that the installation of winglets increases both the lift-to-drag ratio and bending moment compared to the clean wing configuration. Among the studied airfoil profiles, NACA 0010 demonstrated the optimum lift-to-drag ratio, showing a 9.5% improvement over the clean wing configuration. Although it is a symmetrical airfoil, the thickness of NACA 0010 contributed to higher lift production and increased bending moment compared to the cambered airfoils (NACA 64-009 and PSU 94-047), which showed approximately 10% improvement in lift-to-drag ratio. While the differences in aerodynamic characteristics between the airfoil profiles were marginal, the overall addition of winglets proved effective in increasing lift and reducing induced drag. The research highlights the significance of airfoil shape and thickness in optimizing winglet performance. Future studies should focus on refining the winglet airfoil profile to maximize the benefits derived from both thickness and cambered shape, aiming to further enhance aerodynamic efficiency.
Parachute Design and Wind Tunnel Testing of Class 10 kg LAPAN UAV Recovery System Herdiana, Dana; M. Ichwanul Hakim, Teuku; M. Pramutadi, Ardanto; Waryoto
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.1050

Abstract

LAPAN (BRIN) has already developed several types of fixed-wing UAVs that are intended to conduct civil applications. The UAV is divided by a weight class, which is 10 kg, 20 kg, and 30 kg in MTOW. In some missions, the UAV can operate in the normal way, take-off and landing by using a small runway. In some other missions, the UAV has to be launched by using a catapult and landing by net because of limited space. In the case where the UAV has to be landed between the trees, the usage of nets is not possible. Therefore the recovery system by using a parachute is designed. The cross-type parachute is designed by using analytical and simulation methods to calculate the descent velocity when the aircraft vertically lands. The descent velocity is derived from structure and payload requirements where the impact when the aircraft touches the ground will not cause damage. The designed parachute was then tested in a LAPAN Low-Speed Tunnel (LLST) to verify the design. The tests are conducted in various Reynolds numbers to observe parachute characteristics at a wide range of velocity. The wind tunnel model which is used in the test has a scale of 1:6. The Result of the simulation and the test shows that the design of the parachute was sufficient to be used as a recovery system for a class 10 kg LAPAN UAV because the descent velocity requirement is fulfilled.
SolaSolar Flare Effect to Sq Variation of Geomagnetic Field Observed at Biak Station from 1992 to 2003 Visca Wellyanita; La Ode, Muhammad Musafar; Ahmad Zulfiana Utama; Mira Juangsih; Siska Filawati; Rizal Suryana; Setyanto Cahyo Pranoto; Yana Robiana; Refina Sri Fitri Wisnu
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.2024.1168

Abstract

We analyzed the dependence of the geomagnetic Sq field variation at the Biak magnetic field observation station using data from a magnetometer from 1992 to 2003. The Biak station is a low magnetic latitude station, making the dominant variation of the magnetic field component that related to ionospheric currents representable by H-component. The Sq field was extracted from the magnetometer data using the 4th Harmonics Fourier decomposition method. This technique was applied to 1-hour average data of the H-component of the magnetic field. To investigate the dependence of the Sq field amplitude on solar flare events, we selected Sq field variations during flare events without magnetic storms. Additionally, before conducting the Fourier decomposition, we applied Dst index correction to the magnetic field variation data to eliminate the effects of magnetospheric currents. The study shows that Sq variation is highly correlated with X-class flares, which are the most energetic type of flares. Conversely, the lowest amplitude is linked to A-class flares with the lowest energy. These findings indicate that X-class flares generate Sq currents and induce the strongest magnetic fields compared to other classes of flares.
Evolution Study Of Solar Like Star τ Ceti Using Mesa Program Mumtahana, Farahhati; Nurzaman, M. Zamzam; Putri, Gerhana Puannandra; Zulfiana, Ahmad
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.2024.1319

Abstract

Tau (τ) Ceti is a G8V class star that has similarities to the sun and several comparable physical properties, although in general its value is smaller and not as active as the sun. Similarities also occur in the planetary system, which has been studied and confirmed to be terrestrial types, four of them were confirmed in the Habitable Zone. This paper aims to study the evolutionary traces of the star Ceti related to the initial studies of its influence on the planetary system through modelling experiments. Interior structure modelling and evolution were carried out with the MESA program. The study of stars belonging to population II begins with the determination of several fundamental parameters obtained from observations such as interferometry and spectroscopy from several references and calculations, which are then used as input in building the model. Static modeling has been carried out by the current condition of the star in the main sequence phase with an age of 9.5 Gyr producing various physical parameters and the division of the star’s atmospheric zone. The evolutionary modelling was carried out up to the Asymptotic Giant Branch (AGB) stage, related to the initial studies of its relationship to the planetary system. Result shows that, without consideration of planetary tidal effect, three of the four planets are likely to be affected by the evolution of τ Ceti. Even though the simulation was only carried out up to the AGB stage, the end history of τ Ceti will be similar to a Solar-mass star, yet over a longer period of time than the Sun.
Implementation of Backprojection Algorithm for Synthetic Aperture Radar Image Processing on Low-Cost Hardware Platform Agus Wiyono; Chasanah, Nurul; Abner Hamonangan, Jefri; Ruhiyat, Abdurrasyid; Rohman, Abdul; Kurniawan, Farohaji; Muksin; Arief Aditya, Satria; Hendra Wahyudi, Agus; Rahayu, Novelita; Arisal, Andria; Setiadi, Bambang
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.2516

Abstract

This work presents the implementation of back-projection algorithm for Synthetic-Aperture Radar (SAR) signals on a low-cost, small, lightweight, and low-power consumption platform: Raspberry Pi. The algorithm is implemented with GNU Octave open-source software and the performance was tested on Raspberry Pi 3B and 4 hardware. For performance comparison, a single-threaded baseline implementation of back-projection is created and then modified to run on several threads on an available multicore processor. Executing a single-threaded code Raspberry PI is too slow for real-time imaging. However, the parallelized version shows computation improvement over the baseline version. We include a discussion of parallel implementation on a single Pi using Octave’s parallel package. This study contributes to the understanding of implementing SAR image processing on affordable single-board platforms with constrained computing resources.
LabVIEW based Ground Monitoring System for RX200 Rohmah, Nurul Fahrizatul; Faisa Lailiyul Mutho'Affifah; Fikana Mahardika Cantri; Ardian Wardhana; Mirza Zulfikar Rahmat
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.2024.2553

Abstract

The implementation and deployment of a comprehensive ground monitoring system for rockets is essential to ensure the safety, efficiency, and success of space missions. Ground monitoring systems for rockets play a crucial role in providing real-time information and analysis of critical parameters during rocket operations, including ground testing and launch operations. The ground monitoring system encompasses various functionalities including the acquisition, processing, visualization, recording and storage of data. The data acquisition process in LabVIEW involves the use of TCP/IP Visa function to collect information. The processing involves various functions such as parsing, flight time calculation, and queue management for efficient data handling and calculations. The data can be recorded and stored using the TDMS function. The system efficiently managed all the received data. This study achieved 90,94% accurate data in processing the entire dataset and obtaining accurate values for calculating flight time. This combination yields precise and dependable data that can be utilized for making real-time decisions, analyzing performance, and evaluating missions after they have been completed.
Stress Analysis of Load Cell Adaptor Designs For The Caliber450mm Solid Rocket Motor Static Test Moranova, Starida; Putro, Idris Eko; Abrizal, Haryadi; Mariani, Lilis; Prianto, Bayu; Hanif, Azizul; Andiarti, Rika; Ekadj, Firza Fadlan
Indonesian Journal of Aerospace Vol. 21 No. 2 (2023): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2023.2669

Abstract

This study presents a structural analysis of two load cell adaptor designs for a caliber-450 mm solid rocket motor. The structural analysis of a C-shape load cell adaptor and the newly designed truncated-cone shape is presented incorporates a 30-degree truncated disc section and varies the thickness to 30 mm, 25 mm, and 20 mm. The numerical simulation using PATRAN reveals that by altering the arm thickness while maintaining the constant hinge thickness, the 30 mm thickness in the disc section yields the best local maximum stress. However, considering the global maximum stress, the 25 mm thickness emerges as the optimal design. The simulation results show that the 25 mm disc section of the load cell adaptor surpasses the aerospace standard safety factor (SF = 1.5) for both local and global maximum stress.
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
Observations of Ionospheric Conditions Over Pontianak During The Partial Solar Eclipse Suraina; Abadi, Prayitno; Yolanda Putra, Angga; Puannandra Putri, Gerhana; Nurmali, Dadang; Nurdiansah, Lambang; Rakhman, Arif; Ednofri; Muzirwan
Indonesian Journal of Aerospace Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.55981/ijoa.2024.2942

Abstract

Solar energy plays a significant role in creating ionospheric layers through photoionization. However, when a solar eclipse occurs, the ionizing radiation from the sun will be obstructed by the moon, resulting in a decrease in ionization processes and a depletion of ionospheric plasma density. Our research examines the effects of two partial solar eclipse events that occurred on December 26, 2019 (Eclipse 1) and April 20, 2023 (Eclipse 2) over Pontianak. We observed changes in foF2 and TEC during these events. Our observations show that foF2 and TEC decreased at the start of a partial eclipse but returned to normal once the eclipse ended. The maximum decrease in foF2 observed was 1.88 MHz for Eclipse 1 and 1.26 MHz for Eclipse 2, while the decreases in TEC were 5.68 and 12.81 TECU for Eclipse 1 and 2 respectively. We noted that geomagnetic activity was quiet during both eclipses, indicating that the reduction in ionospheric parameters (TEC and foF2) is affected by the solar eclipse. During a solar eclipse, the decrease in ionization intensity results in a reduction in electron numbers in the ionospheric layers, leading to a reduction in TEC and foF2.

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