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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 9 Documents
 1 
Search results for , issue "Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara" : 9 Documents clear
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.
MODIFIKASI PERSAMAAN QUATERNION PADA ALGORITMA INS UNTUK APLIKASI ROKET Wiryadinata, Romi; Widada, Wahyu
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

INS algorithm is used to transform the body frame to the inertial frame of the rocket trajectory. The motion of rocket rotation is different from the air plane. The rocket has a faster motion and need a high speed computation. The pitch angle (θ) which is being greater than 90º, there will be a problem and it needs the Quaternion equation to solve the problem. In this study, the Quaternion parameters are always normalized with the same value at the time of initial initialization. The results of this study indicate that the calculation of body frame and inertial frames have similar results and showed accuracy between 0.2 - 1 meter. In the process algorithms in real-time INS will require a high-speed microprocessors to speed up the computing time on an embedded system payload.
ANALISIS DAN OPTIMASI SUDU SKEA 5 KW UNTUK PEMOMPAAN Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

LAPAN Wind Energy Conversion System (WECS) for pumping (SKEA-MARUTO) has a rotor diameter of 4.5 m and 6 number of blades. The blade used is a curved plate area. The result of recalculation has shown that operational condition on 10 m/sec wind speed and 100 rpm rotational speed, the rotor produces 4.74 kW. By assuming of 20% generator losses, the SKEA will produces power of 3.79 kW. To improve this performance to 5 kW, the rotor diameter has to be increased to 6 m. Chord and twist distribution are made similar to the previous design, and remain unchanged. Calculation is made by varying number of blades and blade rotation. At the wind speed of 10 m/sec and the rotational speed of 100 rpm, the SKEA able to produce the power of 6.36 kW.
ANALISIS MANUVER PENYELAMATAN SATELIT PALAPA - D Triharjanto, Robertus Heru; Hutasulut, Hagorly M
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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The paper discusses the analysis on orbit maneuver done to rescue PALAPA-D satellite stranded in high elliptical orbit during its launch in 2009. The purpose of the research is as an exercise for LAPAN and ITB on designing orbit maneuver, especially in the rescue of satellite stranded while approaching its GTO during its launch. The study will gain knowledge on the key factors that make the rescue effort successful. The simulation is done using orbit analysis software STK. Meanwhile, the LM-3 launcher and Spacebus-4000 satellite bus data is taken from internet publication. The result on the life of the satellite is only difference by 1,9% from the one calculated by the satellite manufacturers, Thales Alenia. Therefore, it can be concluded that the analysis has good validity.
NUMERICAL SIMULATION OF UNSTEADY VISCOUS FLOW AROUND AIRSHIP USING VORTEX METHOD Subagyo
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The grid-less Vortex Method has been developed as the tool for the analysis of two-dimensional (2D) and three-dimensional (3D) complex flows in various engineering applications. In the present study, unsteady flows around a slightly complex geometry (bare hull of an airship and body of an airship) at angles incidence α= 10°, 20°, and 30° were investigated by using the vortex method for a high Reynolds number, Re = 3.9105. The flow-pattern, velocity field, coefficient of pressure distribution on the bare hull and the surface of the airship body, and the aerodynamic coefficient were obtained from numerical calculations. A comparison of the numerical results with the experimental observations showed a good agreement.
RANCANGAN AWAL DAN ANALISIS BENTUK SUDU TURBIN ANGIN 50 KW Ginting, Dines
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Wind turbine blade design is done through the process of aerodynamic optimization involving wind speed, blades number and profile, solidity and rotor speed. Three options of 50 kW wind turbine blade shape the will be analyzed, the optimum shape, taper and rectangular. Each blade shape has the distinct complexity and characteristics so that the handling and manufacture, the performance characteristic, the diameter and speed of blades is also different. Maximum performance of the optimum blade shape is higher than the tapered or rectangular shapes so that the diameter of the optimum blade shape is smaller than the tapered or rectangular shapes. On the contrary, handling and manufacture blades with square shape easier than with any shape optimum or taper. The different blade shapes will not cause any disadvantage as far as handling and manufacture of blades that means the blade cost to compensate for this blade shapes effect. The taper blade shape is selected for the wind turbine.
ANALISIS TEGANGAN PADA TABUNG KOMPOSIT SERAT KARBON UNTUK MOTOR ROKET BERDIAMETER 200 MM DENGAN METODE SINGLE LAYER LAMINATED ELEMENT Putra, Ronald Gunawan; Triharjanto, Robertus Heru
Indonesian Journal of Aerospace Vol. 8 No. 2 Desember (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This research analizes rocket RWX 200 motor tube using carbon fiber reinforced for 6 mm thickness in order to optimize the weight. Carbon fiber is chosen due to its mechanical properties such as high strength and stiffness, and high temperature resistance, as the specification needs of the rocket motor tube. Rocket motor tube is manufactured by using weaving method, while the analysis and simulation is calculated by assuming it as laminate with the [0/90]s stacking sequence. From the calculation and simulation, it is determined that the X stress component of the laminates is below the strength of the material, while the Y stress component is beyond the strength of the material. It can be concluded that 900 laminae in each laminates has been failed.

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