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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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The Occurrence Of Geomagnetic Storm In Solar Cycles 23 And 24 And Their Correlation With Cycle Peaks Juangsih, Mira; Nuraeni, Fitri; Ratnasari, Elvina; Hakim, Lukmanul
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

Abstract

The 23rd solar cycle occurred from 1996 to 2008, while the 24th solar cycle occurred from 2009 to 2020. Throughout the cycles there were various solar activities that caused geomagnetic storm such as high speed stream (HSS), co-rotating interaction region (CIR), and coronal mass ejection (CME). By using Disturbance storm time (Dst) index, we identified 243 storms during cycle 23 and 149 storms during cycle 24. The distribution of geomagnetic storms corresponds to the distribution of the solar cycle based on sunspot numbers. The cycle 23 exhibited higher activity with 84 strong to extreme storms compare to cycle 24 which had 22 strong to very strong storms. In both cycles, 65% moderate geomagnetic storms were caused by the high speed stream, whereas 85% of strong geomagnetic storms were caused by CMEs. In this study, both cycles exhibit distinct characteristic in producing geomagnetic storms. The low or high maximum phase of a cycle is not associated with the frequency occurrence of strong to extreme geomagnetic storms; both cycles show comparable results in this regard. However a longer declining phase of solar cycle has more impact on production of more moderate storms
A Review of Absolute Radiometry Calibration Method for Satellite Multispectral Camera while in Orbit Sartika Salaswati; Saputro, Adhi Harmoko; Hasbi, Wahyudi
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.2024.3090

Abstract

Multispectral cameras on satellites are a type of camera that is widely used in satellite remote sensing and has wide applications. Therefore, it is necessary to carry out absolute radiometric calibration to maintain the accuracy of radiometric information in satellite camera images. There are several types of absolute radiometric calibration, including onboard, Rayleigh, vicarious, and cross-calibration. These methods have strengths and weaknesses. Therefore, it is necessary to conduct a literature review to find out which calibration method is appropriate for certain conditions. Based on a literature review, all methods can be used and adapted to the conditions of the satellite. The onboard calibration method is suitable for satellites equipped with calibration instruments. The Rayleigh calibration method is suitable for large FOV cameras with visual wavelengths. The vicarious calibration method is suitable for satellites from countries close to standardized calibration sites. Meanwhile, the cross-calibration method is suitable for satellites cameras that have specifications and conditions close to the reference camera. Therefore, these calibration methods can be carried out together to complement each method.
A Review: Flight Envelope Monitoring and Protection as One of the Flight Safety System Sarah, Annisa; Prajitno, Prawito; Hasim, Fadillah; Hakim, Teuku Mohd Ichwanul
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.2024.4671

Abstract

The development of civil aircraft technology, especially commercial aircraft, is now very advanced and complex. This development is intended to assist the pilots to control aircraft in various flight conditions with the main goal to achieved is flight safety. This literature review will discuss research on the flight warning system, which will support the flight envelope protection system development study, which has been conducted over the past few years. The review includes an analysis of existing literature, case studies of aviation accidents, and the evaluation of flight envelope protection systems in current aircraft models. This review shows that the development of technologies and systems can make a significant contribution to flight safety and pilot situational awareness of flight envelope boundaries, so the possibility of aircraft accidents due to loss of control can be reduced
Potentially Habitable Terrestrial Exoplanets based on the Habitability Index for Transiting Exoplanets (HITE) Value Rozzykin, Achmad Zainur; Lomban, Claudia Amelia; Ikhsan, Muhammad Isnaenda
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.2025.5505

Abstract

In-depth exploration of exoplanet habitability involves a crucial screening processto identify a subset with the potential for sustaining life. The Habitability Index for TransitingExoplanets (HITE) emerges as a vital tool, quantifying a planet’s habitability byassessing the probability of it having a solid surface and liquid water. Represented bythe symbol H, the index assigns values on a scale from 0 to 1. The closer the value to 1,the greater the potential for habitability. H integrates parameters derived from transitdata, encompassing orbital period, transit depth, duration, surface gravity, radius, andeffective temperature of the host star. Through the Virtual Planetary Laboratory (VPL),the calculation of H is executed for exoplanets with terrestrial mass (0.3–10 M⊕) sourcedfrom the Transiting Exoplanet Survey Satellite (TESS) and K2 missions. The results showthat the exoplanets with the highest H values are TOI-700 d from TESS, with a value of0.95202. Of the 228 planets examined, around 9.21% are identified as potentially habitable.
Optimization of Powered Landing Control for Reusable Rockets Using Softmax DDGN Rafika Arum Sari; Muhammad Hadi Widanto; Imron Rosadi
Indonesian Journal of Aerospace Vol. 22 No. 2 (2024): Indonesian Journal Of Aerospace
Publisher : BRIN Publishing

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Abstract

This research presented a novel approach to optimize powered landing control on reusable rockets by using Softmax Double Deep Q-Networks (DDQN). We combined the advantages of Double DQN with Softmax exploration and curriculum learning to achieve precise and efficient landing control. Through extensive experiments in a specially developed 2D simulation environment, our method achieves improved landing accuracy by 37% (reduced final position error from 2.4 m to 1.5 m), better fuel efficiency by 28% (reduced average fuel consumption from 850 kg to 612 kg per landing), and improved adaptability to initial conditions (improved successful landing rate from 76% to 94% across a wide range of altitudes and initial orientations) compared to traditional PID control methods. The results showed that the curriculum learning method significantly outperformed the non-curriculum approach, achieving 27% higher average awards (11.97 vs. 8.61) and 60% better performance consistency as measured by standard deviation (0.92 vs. 2.29). Both Softmax and ε-greedy exploration strategies proved effective with curriculum learning, with ε-greedy DDQN achieving the highest average award of 11.97. This approach allows for higher precision rocket landings while reducing operational costs through.
Comparative Performance of U-Net CNN in Multi-Class Aircraft Segmentation and Classification Using Polygon and Bounding Box Annotations Sitanggang, Rivilyo Mangolat Rizky; Dani, Wa Ode Dianita Putri Suaiba; Setiadi, Bambang; Kuntjoro, Yanif Dwi
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.2025.8155

Abstract

Recent advancements in deep learning have revolutionized image processingtasks such as segmentation and classification. This study investigates theperformance of U- Net-CNN models in multi-class aircraft segmentation andclassification using polygon and bounding box annotations. Military aircraftclassification is crucial for defense applications, as it aids in rapid and accuratedecision-making during critical missions. This study investigates howthese annotation methods affect training time, segmentation accuracy, andclassification performance in multi-class segmentation and classification tasksinvolving military aircraft. The research compares polygon and bounding boxmethods to evaluate their effectiveness in capturing object details and computationalefficiency. While polygon annotations achieved superior precision witha mean test accuracy of 0.987 and lower loss of 0.041, bounding boxes excelledin computational efficiency. Future research should expand datasets and exploreadditional annotation techniques to further generalize these findings.
A Corotational Formulation For Geometrically Nonlinear Dynamics of 2D Flexible Beams Andria, Novi; Zuhal, Lavi Rizki; Muhammad, Hari; Gunawan, Leonardo
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.2024.8949

Abstract

A simple and efficient 2D corotational formulation for dynamic analysis of geometrically nonlinear flexible beam is presented in this paper. The corotational approach can easily facilitate the evaluation of internal elactic forces by introducing an element frame to separate rigid body motion and the deformational part. In the present study, the Euler-Bernoulli beam models with simple geometric stiffness matrix is employed and Newmark’s implicit time-stepping scheme with iterative predictor-corrector algorithm is adopted. The validity and efficiency of the present corotational formulation are verified by simulating three numerical examples. Despite its simple numerical implementation, simulation results confirms that the proposed formulation is highly accurate and efficient in simulating flexible beams undergoing large deformation.
Fuel Efficiency Comparison of PBN and ILS Approach Procedures at Sam Ratulangi Airport M'Azzuri, Banni Yulia; Indriyanto, Toto; Sembiring, Javensius
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.2024.8968

Abstract

This study evaluates the efficiency of approach procedures at Sam Ratulangi International Airport-Manado by comparing Required Navigation Performance (RNP) under Performance-Based Navigation (PBN) with the Instrument Landing System (ILS) as a conventional procedure. A simulation using the BlueSky ATM Simulator was conducted with 30 aircraft instances for each approach, utilizing real-time FlightRadar24 speed data to ensure operational realism. The analysis focused on three key metrics: distance flown, time spent, and fuel consumption. Results show that implementing of PBN procedures reduces distance flown by 15%, flight time by 15% and fuel consumption by 14% compared to ILS, demonstrating improved operational efficiency. This research provides a quantitative assessment of PBN systems’ effectiveness in optimizing approach procedures, supporting aviation sustainability, and reducing operational costs.
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.
Flight Control Design for Rudder Failure Event on Cessna 172 Aircraft Zuhri, Muhammad Rizki
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.2025.9106

Abstract

The Cessna 172, a widely used small commercial aircraft, is renowned for its stabilityin both longitudinal and lateral-directional dimensions. Despite its intrinsic stability, arobust control system is essential to mitigate potential failures, such as rudder malfunctions.This study developed and simulated a control system for the Cessna 172 underrudder failure conditions, relying solely on aileron input for heading control. Using a linearstate-space approach implemented in Matlab/Simulink, the control system incorporatedyaw damping, roll damping, and heading hold for stability and waypoint tracking. Initialsimulations showed that the controller could guide the aircraft to the destination waypointbut exhibited significant deviations of up to 20% under constant rudder inputs. Controllermodification to the PID controller significantly improved performance, reducing deviationsto a maximum of only 0.1% for ±5° rudder input. These results demonstrate the effectivenessof the proposed control system in compensating for rudder failure, though slightoscillations observed at the start of the trajectory suggest the need for further refinement.This research underscores the potential for adaptive and unconventional control methodsto enhance safety and reliability in small aircraft operations.

Page 3 of 37 | Total Record : 364

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