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Jurnal Teknologi Dirgantara
Published by Lembaga Penerbangan dan Antariksa Nasional
ISSN : 14128063     EISSN : 25977849     DOI : https://doi.org/10.30536
Core Subject : Science, Engineering,
Aerospace Engineering Chemical Engineering, Chemistry & Bioengineering Computer Science & IT Mechanical Engineering Physics
Jurnal Teknologi Dirgantara (Journal of Aerospace Technology) is an Indonesian accredited scientific publication that covers topics of Rocket, satellite, and aeronautics technology, as well as a spin-off from aerospace technology, such as aerodynamics, astronautics, aerospace structure, power and thermal system of satellites, flight controls. Propulsion and energetic technologies, such as propellant, rocket static-test, thermodynamics of propulsion system. Launch vehicle technology and space operations, such as satellite telecommunication systems, space payloads, and ground station technologies.
Arjuna Subject : Teknik (semua kategori) - Teknik Ruang Angkasa
Articles 333 Documents
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Identification of Flow-Induced Noise Sources on Two-Dimensional High Lift Devices of Commuter Aircraft Arifin Rasyadi Soemaryanto; Muhammad Fajar; Teuku M Ichwanul Hakim; Sinung Tirtha Pinindriya; Kurnia Hidayat
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3500

Abstract

A numerical predictive tool of flow induced noise generated by deployed high-lift devices of commuter aircraft is presented in this paper. The aircraft high-lift devices are consisting of vane and flap component. The aim of this study is to identify the sources of flow induced noise on the wing and flap cross-section of the aircraft. This study is investigated only two-dimensional effects and two configuration of flap deflection. A numerical computation is carried out using a CFD software with Large Eddy Simulation fluid turbulence model and Ffowcs-Williams & Hawkings analogy for acoustic prediction. Several sound receivers have been installed on far-field and near-field region of the wing-vane-flap cross-section of aircraft to measure the sound spectra. It has been identified that on the cavity of wing and vane-flap cross-section has the highest sound pressure level than another region. There is a vortical separation and shear layer which is contributed to the generation of sound emission downward the cross-section
Integrated Quality Analysis Method of Aluminum for Composite Propellant Production Hamonangan Rekso Diputro Sitompul; Heri Budi Wibowo; Luthfia Hajar Abdillah; Retno Ardianingsih; Afni Restasari; Rika Suwana Budi; Kendra Hartaya; Mohamad Baiquni
Jurnal Teknologi Dirgantara Vol 19, No 2 (2021)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2021.v19.a3655

Abstract

Quality analysis of Aluminum powder for solid fuel composite propellant was carried out to determine the critical parameters of the composite propellant characteristics. Two types of aluminum were analyzed for quality, including bulk density and true density using the Archimedes principle, particle shape, and size using SEM (Scanning Electron Microscope), crystallinity, and purity using XRD (Xray Diffraction), particle area with BET (Brunnauer-Emmet-Teller) and BJH  (Barret-Joyner-Halenda) adsorption isotherm. To test the composite propellant made with 87.5% solid content and 18% AL content, then tested the characteristics of the propellant. The results of the analysis of the quality of aluminum for composite propellant raw materials have a very large influence on the quality of the resulting propellant, so an integrated, quick, and efficient quality analysis is needed. The critical parameters of Aluminum quality as propellant fuel are density, purity, particle shape and size, porosity/surface area, and crystallinity. Fast and efficient integrated analysis can be performed using new instruments, such as shape and size analysis with SEM, purity and crystallinity analysis with XRD, density analysis with a densitometer. AL2 which have smaller particle size, better density and shape parameters value, less pores and surface area than AL1, can be used to produce a higher quality composite propellant. 
Frequency Mapping of Square Head Expander for Vibration Testing Mikhael Gilang Pribadi Putra Pratama; Muksin Muksin; Yusuf Giri Wijaya; Nur M. Ula; Agus Harno Nurdin Syah
Jurnal Teknologi Dirgantara Vol 20, No 1 (2022)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3709

Abstract

Head expander is a component of an electro-dynamic shaker used for vibration tests in the vertical direction for large-size specimens. This study aims to determine the natural frequency distribution of the head expander across a certain number of predetermined points. This distribution map needs to be known to determine the better placement of future specimens on the head expander. In this study, the determination of natural frequency distribution is done through harmonic analysis (simulation) and experiment to form a contrast between the head expander's ideal condition and the actual condition. The frequency range in the middle of the Head Expander has almost the same value for both data types at 1550-1650 Hz. These results recommend that the best sample placement is in the middle of the Head Expander. The difference between the experimental and simulation low points has a not too far difference, which is 62.5 Hz. In contrast, at the highest value, the two have a quite far difference, which is 180.27 Hz. this difference can be caused by the improper installation of sensors on the Head Expander at certain points.
Investigation of the Mechanical Properties of Vinyl ester Carbon Composites Through Immersion in Seawater and Freshwater Using the VARI (Vacuum Assisted Resin Infusion) Method Nurul Lailatul Muzayadah; Taufiq S. Nurtiasto; Kosim Abdurrahman; Afid Nugroho; Nur M. Ula; Rezky Agung P.; Redha A. Ramadhan; Rozi Hendrawan
Jurnal Teknologi Dirgantara Vol 20, No 1 (2022)
Publisher : National Institute of Aeronautics and Space - LAPAN

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 Eries Bagita Jayanti; Fuad Surastyo Pranoto; Singgih Satrio Wibowo
Jurnal Teknologi Dirgantara Vol 20, No 1 (2022)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
Risk Analysis of Operation Igniter Technology System For Rocket Motor X Widianto Nugroho; Hendrana Tjahjadi; Y.H Yogaswara; Evie Lestariana
Jurnal Teknologi Dirgantara Vol 20, No 1 (2022)
Publisher : National Institute of Aeronautics and Space - LAPAN

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 Haqq; Rahmat A. Duhri; Endro A.; Idris E. Putro; Arif N. Hakim
Jurnal Teknologi Dirgantara Vol 20, No 1 (2022)
Publisher : National Institute of Aeronautics and Space - LAPAN

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 Sartika Salaswati
Jurnal Teknologi Dirgantara Vol 20, No 1 (2022)
Publisher : National Institute of Aeronautics and Space - LAPAN

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.
Indonesian Sovereignty Rights in the Case of Entry of Malaysian DA62 Aircraft G-DVOR into Indonesian Territory Siregar, El Renova Ed.; Prabandari, Adya Paramita
Jurnal Teknologi Dirgantara Vol 20, No 2 (2022): Jurnal Teknologi Dirgantara
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3936

Abstract

The entry of a DA62 aircraft into Indonesian territory from Malaysia has sparked a debate regarding Indonesia's air sovereignty. Indonesia's action to intercept the aircraft before releasing it back has become an interesting subject of research in air law as issues of air sovereignty have not often been the focus of study. Through an understanding of the Chicago Convention on International Civil Aviation and the United Nations Convention on the Law of the Sea (UNCLOS) 1982, it is hoped that an understanding of this issue can guide Indonesia's actions and policies. The research findings using a normative juridical method suggest that Indonesia has legally justifiable grounds to intercept the Malaysian aircraft, and Indonesia's action in releasing the aircraft is in accordance with Indonesia's principles of international politics. However, in the future, challenges regarding historical territory and other issues related to controversies over peaceful routes and outer limits of maritime boundaries have yet to find a middle ground acceptable to all parties.
Flatwise Testing Modeling Study On Aluminium Honeycomb Panel Ramayanti, Sri
Jurnal Teknologi Dirgantara Vol 20, No 2 (2022): Jurnal Teknologi Dirgantara
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2022.v20.a3937

Abstract

Honeycomb sandwich structures are widely used in space applications due to their exceptional performance. Extensive research has been conducted on the response of honeycomb structures to various external loads. The out-of-plane strength, including compression and tensile properties, is a critical aspect of honeycomb structures. Despite some experimental and numerical studies, research specifically addressing the tensile direction, such as flatwise tensile testing in honeycombs, remains limited. This testing focuses on the bond strength between the face sheets and the honeycomb core, as well as the tensile strength of the core itself. Utilizing finite element analysis (FEA) has proven effective for characterizing honeycomb structures under various load conditions. However, the complex geometry of the core requires an enormous number of elements, increasing computation times. Thus, simplifying the model by replacing the hexagonal geometry with a homogenized solid layer with effective material properties is necessary. This study focuses on flatwise tensile testing of aluminum honeycomb using different modeling approaches: discrete, continuum, and equivalent plate models. The discrete model serves as the reference due to its detailed structural representation. The continuum-Gibson model, while reasonably accurate in stress estimation, tends to overestimate displacement. Both equivalent models, Hoff and Reissner, significantly overestimate displacement, with Hoff underestimating stress and Reissner overestimating it. In contrast, equivalent models offer insights, but their accuracy varies, necessitating further calibration for precise predictions. Future research should validate these simulation results with real tests

Page 33 of 34 | Total Record : 333

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