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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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Cosmic Ray Intensity Analysis Based on the Earth’s Latitude and Hemisphere Putri, Annisa Novia Indra
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.2025.9551

Abstract

The interaction between cosmic rays and solar activity has been extensively investigated,particularly in relation to how solar phenomena modulate cosmic ray intensity inthe heliosphere. The strength of cosmic rays absorbed by the Earth’s hemisphere is notuniform across the Northern Hemisphere (NH) and Southern Hemisphere (SH). This studywill include an investigation of cosmic ray intensity as recorded at various latitudes andhemispheres of the Earth. We employed nine cosmic ray stations in each NH and SH,separated into three types of latitudes: low, middle, and high. The method of percentagechange in cosmic ray intensity was used, which was evaluated during the HalloweenStorm phenomenon on October 29-30, 2003. The results showed that cosmic ray intensitydecreased more at high latitudes than at low latitudes in both hemispheres (NH and SH).Furthermore, the reduction in cosmic ray intensity observed in the NH was approximately1% greater than that observed in the SH. This can be attributed to the Rc value’s dependenceon latitude, variations in geomagnetic activity under different Interplanetary MagneticField (IMF) circumstances, and interplanetary space parameters such as the tilt of theHeliospheric Current Sheet (HCS).
Mass Optimization of Rocket Nozzles Using Ablative Materials: A Case Study on Indonesian Sounding Rockets Abrizal, Haryadi; Juwono, Ariadne Laksmidevi; Jihad, Bagus Hayatul
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.2025.11394

Abstract

This study presents a comprehensive redesign of the RX450 sounding rocket nozzleaimed at reducing mass while maintaining thermal and structural integrity. The baselinedesign, characterized by heavy steel casing and monolithic graphite liners, imposes significantlimitations on payload capacity and flight performance due to its weight and thermalmanagement challenges. The proposed design replaces the divergent section’s steel casingwith a combination of ablative silica-phenolic composite liners and aluminum 6061 structuralsupport, achieving a substantial mass reduction from approximately 59 kg to 14.5 kgin this critical region. Thermal simulations demonstrate that the addition of a glass-phenolicinsulation layer effectively limits heat transfer to the metallic casing, allowing for thinnerstructural components without compromising safety. Structural analyses confirm thatboth steel and aluminum sections maintain high safety factors under operational loads.Comparative evaluations of alternative configurations further highlight the benefits of advancedcomposite materials and innovative structural concepts, with the lightest modelreducing total nozzle mass by around 40% compared to the baseline. While these resultsare based on literature-derived properties and simplified assumptions, they underscore thepotential of integrating ablative composites and lightweight metals to enhance rocket nozzleperformance. Future work will focus on detailed thermochemical modeling, experimentalvalidation, and full-scale testing to confirm thermal-structural behavior and erosionrates. Overall, this study supports Indonesia’s strategic objective of advancing indigenousrocket technology through accessible, high-performance materials and design innovations.
Front Pages JTD Vol 17 no.2 Desember 2019 Jurnal, Redaksi
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.a3283

Abstract

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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.
AnaLISIS KESELAMATAN RADIASI GEDUNG LABORATORIUM RADIOGRAFI PUSTEKROKET LAPAN SECARA TEKNIS DAN LEGAL Budi, Rika Suwana; Syaifudin, Rofiq
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.a3208

Abstract

Analisis keamanan radiasi diperlukan untuk mengevaluasi tingkat keamanan radiasi dan tindakan yang diperlukan pada saat bekerja atau berada dilingkungan dengan radiasi tinggi. Hasil pengujian tingkat kebocoran radiasi menunjukkan bahwa gedung laboratorium uji radiasi memerlukan penambahan dinding perisai.
ANALISIS PENENTUAN POWER LOADING PADA DESAIN AWAL PESAWAT TERBANG TANPA AWAK LSU-05 NG Atmasari, Novita; Jayanti, Eries Bagita; Ula, Nur Mufidatul; Ramadiansyah, M. Luthfi; Ramadhan , Redha Akbar; Suseno, Prasetyo Ardi Probo; Rizaldi, Ardian; Hidayat, Kurnia; Septiyana , Angga
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.a3162

Abstract

Penelitian ini berfokus pada analisa penentuan power loading pada awal desain pesawat LSU-05 NG. Dengan menentukan power loading maka kebutuhan daya engine untuk pesawat LSU-05 NG dapat diestimasi. Artinya pemilihan engine dapat dilakukan sehingga menghasilkan gaya dorong agar pesawat dapat melakukan misi pemantauan dan foto udara dengan baik. Metode yang digunakan untuk analisa penentuan power loading adalah teknik Matching Chart atau Matching Plot dengan memilih titik optimal dari lima konstrain yaitu jarak take-off, climb rate, stall speed, cruise speed, dan landing. Hasil penelitian menunjukkan bahwa dengan massa 85 kg dan luas sayap 3,22 m2 pesawat LSU-05 NG membutuhkan daya 9.7 hp. Penjelasan lebih detail akan dijabarkan pada bagian selanjutnya.
Effect Of Rubber Damper Stiffness And Tire Pressure To Reduce Ground Reaction Load Factor On Main Landing Gear Using Multi-Body Simulation (MBS) Rigid Model Hidayat, Dony; Istiyanto, Jos; Marta, Aryandi; Hidayat, Kurnia; Sumarsono, Danardono Agus
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.a3131

Abstract

Landing Gear Drop Test (LGDT) utilizes the apparatus requiring a substantial time and cost. Virtual LGDT (vLGDT) using MSC ADAMS software is one of the solutions for initial stage to testing landing gear. From simulation with vsink 1.7 m/s and load 22000 N obtained contact/impact force that ensue in MSC ADAMS was 73650 N, while from experimental was 73612 N. The difference between vLGDT and LGDT result is 0.05 %. To obtain ground reaction load factor below 3 in vsink = 3.05 m/s, the rubber damper should have stiffness in the range of 1900 - 2100 N/mm and for the tire pressure of 60 - 65 psi.
LOW COST EMBEDDED CONTROLLER SIMULATION FOR MISSILE IN REAL-TIME ENVIRONMENT Putro, Idris E.; Septanto, Harry
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.a3159

Abstract

This paper focuses on the development of real-time environment for low cost embedded system to control flight performance of missile. Real-time simulation is generated by using xPC target so that standalone target boot can be developed, and target PCs can be simulated in real-time. Two PCs and single board computers (SBCs) are required to configure the host and standalone target respectively. The host PCs are used to control the target PCs while these target PCs run simultaneously in real-time. Target PCs are divided into plant platform and controller platform. Plant platform represents missile dynamics model, while control algorithm is compiled to the other system as controller platform. Linear control synthesis will be implemented for maintaining flight stability of missile using optimal control approach based linear quadratic regulator (LQR). This real-time system should resemble the environment of future flight test.
Pemilihan Airfoil Pesawat Terbang Tanpa Awak LSU-05 NG dengan Menggunakan Analytical Hierarchy Process Hidayat, Kurnia; Rizaldi, Ardian; Septiyana, Angga; Ramadiansyah, M. Luthfi; Ramadhan , Redha Akbar; Suseno, Prasetyo Ardi Probo; Jayanti, Eries Bagita; Atmasari, Novita; Nurtiasto , Taufiq Satrio
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.a3161

Abstract

Pada perancangan pesawat terbang tanpa awak, pemilihan airfoil sangat penting untuk meningkatkan performa pesawat. Airfoil dipilih berdasarkan karakteristik geometri dan performa aerodinamikanya. Penelitian ini membahas tentang pemilihan airfoil dengan banyak kriteria berdasarkan karakteristik masing-masing airfoil. Pada tahap awal, sebanyak 1504 airfoil tersaring menjadi 5 airfoil terpilih. Airfoil tersebut dianalisis berdasarkan 7 kriteria utama, yaitu Camber, Thickness, Manufacturability, Max C_L, C_(L_0 ), Max C_L angle, dan Max L/D. Berdasarkan analisis tersebut, FX 76-MP-160 terpilih sebagai airfoil terbaik untuk pesawat terbang tanpa awak yang dirancang.
PRELIMINARY THERMAL CONTROL DESIGN ANALYSIS OF LAPAN SAR-MICROSATELLITE DEPLOYABLE SOLAR ARRAY PANEL USING ONE NODAL METHODE Budiantoro, Poki Agung; Fauzi, Ahmad
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.a3155

Abstract

LAPAN SAR-Microsatellite is the first LAPAN micro satellite being developed and planned to carry a Synthetic Aperture Radar (SAR) payload. Different from optical satellites that have been developed, LAPAN SAR-Microsatellite requires a lot more power. Solar array panels are needed to generate solar radiation into electrical energy which is used by all of subsystem satellite as energy to turn on and turn off all of components. More larger the area of solar array panel, more greater to the energy obtanied. Therefore, the needed of deployable solar array panel is a must caused by the dimension of the main body structur (MBS) are not large enough. Solar cells will experience a decrease in efficiency if they experience excessive heat. If there is a decrease in efficiency in the solar cell, it will have an impact on the decrease in power produced. The purpose of this study is to conduct thermal design on solar panels to maintain temperature according to their working temperature. Calculations are carried out on the temperature of solar array panel with various optical properties in the upper and lower panel that best which will be use using one nodal analysis methode According to the calculation result from all of the designs passive thermal control system on this study show that Design-5 is the best thermal control design which can be used for LAPAN SAR-microsatellite deployable solar array panel which α=0.24 at the top and ε=0.9 at the bottom surface of solar array panel.

Page 4 of 37 | Total Record : 364

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