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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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ANALISIS DAN PENGUJIAN SISTEM BATERAI SATELIT LAPAN-A2/ORARI (ANALYSIS AND TEST OF LAPAN A2/ORARI SATELLITE BATTERY SYSTEM) Karim, Abdul Karim; Hasbi, Wahyudi
Indonesian Journal of Aerospace Vol. 11 No. 2 Desember (2013): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Penyimpanan daya listrik dalam baterai sangat diperlukan sistem satelit sebagai pasokan daya satelit pada saat orbitnya tidak mengalami cahaya matahari (eclipse). Untuk memenuhi kebutuhan tersebut sistem LAPAN-A2/ORARI dilengkapi oleh 3 buah paket baterai dengan spesifikasi total daya 18,3 Ah pada tegangan nominal 15 Volt. Dalam makalah ini akan dijelaskan analisis hasil pengujian baterai dengan cara charging dan discharging. Data daya listrik setiap baterai akan direkam menggunakan perangkat lunak dan kemudian akan dilakukan analisis data. Hasil analisis menunjukan total kapasitas baterai satelit LAPAN-A2/ORARI adalah 18,287 Ah/ 307,221 Wh dan nilai operasional adalah 18,078 Ah/303,710 Wh pada tegangan 16,8 Volt.
Investigation of the Mechanical Properties of Vinyl ester Carbon Composites Through Immersion in Seawater and Freshwater Using the VARI (Vacuum Assisted Resin Infusion) Method Muzayadah, Nurul Lailatul; Nurtiasto, Taufiq Satrio; Abdurrahman, Kosim; Nugroho, Afid; Wandono, Fajar Ari; Ula, Nur Mufidatul; P, Rezky Agung; Ramadhan , Redha Akbar; Hendrawan, Rozi
Indonesian Journal of Aerospace Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3579

Abstract

The carbon-vinyl ester composites have made for the development of the base material for Amphibious floats. The properties of this composite have strength, lighter weight and resistant to corrosion. This study was aimed to report the effect of two different water immersion treatment namely seawater and freshwater on the mechanical properties of composite made from fiber twill and vinyl ester resin using the vacuum assisted resin infusion (VARI) method. Experiments were carried out on tensile, compressive, and shear tests. The specimens were immersed in seawater and freshwater for ten days. The results have shown that Ultimate Tensile Strength of the composite with seawater immersion declined 1.27% compare with the composite without immersion treatment, while the composite in freshwater got greater 3.56%. The decrement of compressive and shear strength was more significant than tensile strength. The compressive strength declined 17.89% and 16.7% for freshwater and seawater treatment, respectively. The shear strength decreased 27.87 % and 25.77% for freshwater and seawater treatment, respectively
Identification of Aircraft Parameters in the Lateral-Directional Flight Dimension with Variation of Control Input Jayanti, Eries Bagita; Pranoto, Fuad Surastyo; Wibowo, Singgih Satrio
Indonesian Journal of Aerospace Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3658

Abstract

In this research, the process of identifying aircraft parameters is carried out for the lateral-directional dimension by notice the variations of the given control surface deflection input. The inputs are pulse, doublet and 3-2-1-1. Among the input forms, it is not known which form is most suitable for the lateral-directional dimension. Simulation is done by varying the input deflection control surface and simulation time. The input given is deflection of the aileron and rudder control surfaces. This research uses the equation error method with the ordinary least square estimation technique. The purpose of this research to identify the most suitable input for the identification of parameters in the lateral-directional dimension and to observe the effect of simulation time. The aircraft used is the Lockheed C-5 Galaxy. The simulation results show that the combination of the 3-2-1-1 input form in the aileron deflection surface and the input pulse shape on the rudder has an error value of about 0.09. This value is smaller among all cases seen from the error matrix A. Based on that, the combination of the two inputs is the most suitable for the lateral-directional dimension than the other inputs that have been given.
ANALISIS BEBAN HENTAK STRUKTUR PENYANGGA LANDING GEAR PESAWAT NIR AWAK LSU03 (SHOCK LOAD ANALYSIZES FOR THE LSU03 UAVS LANDING GEAR SUPPORT STRUCTURE) Bintoro, Atik
Indonesian Journal of Aerospace Vol. 11 No. 2 Desember (2013): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Pesawat nir awak LSU03 adalah pesawat nir awak yang dikembangkan oleh Lapan, untuk misi pembawa muatan kamera foto maupun video. Dalam operasinya, LSU03 akan melalui siklus terbang dan mendarat dengan frekuensi yang cukup tinggi, khususnya untuk pengisian bahan bakar dan perawatan. Pada saat awal pendaratan di landasan udara, terjadi beban hentak yang dapat mempengaruhi keandalan struktur. Melalui metode analitis persamaan beban hentak, masukan data konfigurasi pesawat nir awak LSU03, dan pernyataan misi karakteristik, telah dilakukan penelitian dan analisis beban hentak struktur penyangga landing gear pesawat nir awak LSU03 pada saat awal pendaratan di landasan. Dari analisis hasil penelitian diketahui bahwa struktur penyangga yang berukuran tebal 2 mm, lebar 8 mm, terbuat dari komposit jenis serat e-glass mampu menerima beban hentak tersebut.
Risk Analysis of Operation Igniter Technology System For Rocket Motor X Nugroho, Widianto; Tjahjadi, Hendrana; Yogaswara, Y. H.; Lestariana, Evie
Indonesian Journal of Aerospace Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3708

Abstract

This study discusses risk assessment, and the results of the analysis on the ignition system used on the X rocket. The purpose of this study was to obtain a risk analysis obtained when operating the ignition system on the X rocket. This study used HIRADC (Hazard Identification, Risk Assessment and Determining Control) with a qualitative explanation. The results of the risk assessment in the X rocket motor testing process on the application of the ignition system, there are 10 risks in activities consisting of 8 activities that have a "low" risk level, while the other 2 have a "High" risk level. Caused by probability 1 and severity 4 which can result in device explosion as well as death of the user. The scope of the next assessment is instruments risk assessment, based on the research conducted, the results obtained from the risk assessment are 13 risks of instruments failure, consisting of 9 risks with a "low" risk value. Meanwhile, there are 2 "moderate" risks, namely a short circuit in the cable and the casing does not catch fire which can result in serious injury. Other sectors that have 2 high risk "High" are found to be at risk of not being grounded which can result in static electricity not going to ground, premature ignition during installation, explosion, which can cause death.
Identification of Flight Performance RX-450 Series-5 Hakiki, Hakiki; Duhri, Rahmat A.; A., Endro; Putro, Idris E.; Hakim, Arif N.
Indonesian Journal of Aerospace Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3686

Abstract

The performance of rocket flight can be evaluated from flight test data. The difference between flight prediction simulation and flight test data will indicate the accuracy of rocket identification model. Several factors cause rocket flight test deviated from flight prediction. Atmospheric disturbances and thrust scale are major factors causing inaccuracy rocket model. Another obstacle encountered is lack of flight data measured from flight test although there are still several data are obtained from accelerometer, altitude sensor, and GPS. Rocket performance identification can be obtained by conducting simulation of flight test data. This paper addresses identification of RX-450 series-5 in terms of flight performance. Thrust profile is generated from accelerometer recording data, and this parameter become an input for rocket simulation. The wind data is treated as atmospheric disturbance. The wind data is augmented by GPS on air balloon, and further processed become wind speed and win direction. Comparison both data can be explained as follow: During boost-phase, flight test data of the rocket shows maximum acceleration of 14.5g, on the other hand flight identification gives 13.4g. Rocket flies for 157.36 s in flight test whereas rocket identification predicts the max of flight time is 162.8 s. The rocket has max-range in 86.06 km measured by GPS data whereas flight identification estimates the max-range is 82.78 km. The flight identification indicates that the roket was deviated 6.25° from initial azimuth of the launcher direction. This 6.25° of deviation leads the rocket flies in Y-direction with the distance of 9.02 km. Flight test data shows that the rocket slides its direction 6° to the right of the initial launch azimuth.
Analysis of the Atmospheric Effects on the Vicarious Calibration of LAPAN-A3/IPB Satellite Multispectral Camera in Jaddih Hill Madura Salaswati, Sartika; Hakim, Patria Rachman; Syafrudin, A Hadi; Herawan, Agus; Hartono, Rommy; Utama, Satriya; Yatim, Rakhmat; Ardinal, Rifki; Pamadi, Bambang Sigit
Indonesian Journal of Aerospace Vol. 20 No. 1 (2022): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3652

Abstract

Line Imager Space Application (LISA) is a multispectral camera on the LAPAN-A3/IPB satellite. This camera is the main payload that supports the remote sensing mission of the LAPAN-A3/IPB satellite. The important role of LISA requires this camera has a good quality standard. Vicarious calibration is one of the ways to get this quality. Vicarious calibration of LISA in the Jaddih hill area has been done, but the process has not used aerosol optical depth data. Therefore, further research was conducted to determine the effect of AOD data on the radiance coefficient. This paper describes the vicarious calibration of LISA using three types of data, namely LISA image data, reflectance data, and aerosol optical depth data of the Jaddih hill area. From the three data, the radiance coefficient for each LISA channel was obtained. The results show that there is an effect of AOD data on the radiance coefficient, but the effect is not too significant. The difference of the radiance coefficients for each channel is not too far away, that is 0.00008 for red channels, 0.00011 for green channels, 0.00039 for blue channels, and 0.00011 for NIR channels. Besides, the results of the radiance coefficient from previous studies indicate that the radiance coefficient is generated from this study is quite precise so that it can be applied for LISA imagery.
PERANCANGAN AKUISISI DATA SUMBER INFRA MERAH SEBAGAI AWAL PENELITIAN SISTEM SEEKER BERBASIS INFRA MERAH Wahyudi, Agus Hendra; Prabowo, Gunawan S
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Diagnostic tool in the thermal imaging using the thermovision has been developed to characterize the plume gas of solid AP-HTPB rocket propellant. The data Acquisition of the infrared source has been developed based on microcontroller and labview as a Software. This software can increase the capability of the thermovision camera with the real time process. Infrared source BaF2 was used as an object and this test has given the result: voltage 1.8 volt, thermal 390 Kelvin, and can be converted to 7-8 um wavelength. In the future, this system can be integrated with the actuator robotic or the fin of the rocket.
SELEKSI PEMILIHAN MATERIAL UNTUK TABUNG ROKET RX 420 Sumaraw, Elvis A
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

A Calculation to select the material being used for RX 420 rocket has been conducted. The selection is applied to 3 kinds of tube material i.e. SS 17-7 PH steel, ASTM A312 AISI TP304L steel and AISI 4130 steel. By inputing data of tensile strength material, strain acting on the tube, tube diameter and tube length; the size of the tube can be calculated. The thicker tube and the lightest tube are then selected to be used. From the calculation result of SS 17-7 PH steel material, the tube with the thick of 1,8 mm (safety factor, k=2) with the tube weight of 85,458 kg are the most convenient materials applied; due to the thicker (1,8mm) and the lightest (85,458 kg) with the tensile strength of 900 MPa. If ASTM A312 AISI TP304L steel material is used , then the tube thick proposed is 2,8 mm, with the tube weight of 131,7 kg. If AISI 4130 steel material is used, then the tube proposed is 3 mm, with the tube weight of 142,4 kg.
PENERAPAN FEM UNTUK MENENTUKAN MATERIAL KOMPONEN PROPULSI ROKET RKX-10C16 Samosir, Ganda
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

One of the most important rocket propulsion components is nozzle where the thermal energy is converted to kinetics and finally became the mechanics energy in the form of thrust. During the combustion process of the propellant, the nozzle will be influenced by some constraints, namely the pressure and the thermal. The nozzles material chosen, must than be strength enough to minimize those constraints, but still, the nozzle must be weight enough. The Finite Element Method (FEM) used to analyze the nozzles structure strength must be applied to those constraints separately. The result is then compared to the technical specification of the nozzle material chosen. From the static test of the rocket 100 mm clases, it is known that the operating pressure is 46 kg/cm2= 4,51 MPa and 3000ºC of temperature but about 90 % are absorbed by the tube liners (inhibitor). If the calculated safety factor minimum, min F S ≥ 1, the selected material then meets the requirement. Basically, the rocket nozzle consist of two different materials, the outer side is made from the metal (steel), the inner one is from the graphite, but the calculation in this paper was made to the metal part only. After being well analyzed, we arrive then to the conclusion that the metal part of the nozzle is made from the carbon steel S-45C.

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