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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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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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Abstract

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.
UJI AERODINAMIK MODEL KAPAL BERSAYAP WING IN SURFACE EFFECT SEBAGAI INPUT KAJIAN GERAK PLANNING MENJELANG TAKE-OFF Iskendar; Widodo, A. Farid; Mulyanto, Taufiq; Indiyono, Paulus
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper describes aerodynamic tests (wind tunnel tests) for a model of Wing in Surface Effect Craft 8 seater, WiSE-8. The tests were conducted at UPT-Laboratorium Aero Gasdinamika dan Getaran (LAGG)-BPPT, PUSPIPTEK, Serpong, to determine the performance of the lift and pre-take off craft conditions. This craft model with scale of 1 per 6 was tested with rigid body - upside up - power off method. The profile of craft wing model was aerofoil form, Clark-Y. The craft model test with complete configuration (Wing-Body-Pontoon-Nacelle-Tail) was carried out with the following parameters, wind speed of 20, 30, 40, and 50 m per sec, angle of attack of -6 to 18 degree, yaw angle of 0 degree, ground board height 0-1 m (in respect to prototype value of 0-6 m). Meanwhile,the tests of air flow visualization were carried out by using wool tuft at speed of 40 m per sec. The result of wind tunnel test consisting of CL, CD, CM, and CL-CD was validated by theoritical calculation using Vortex Lattice Method (VLM) and Datcom software. Then this result was evaluated and extrapolated to predict the movement of WiSE-8 in the pre take off performance condition, especially in the longitudinal direction.
ANALISIS THERMAL STRUKTUR SATELIT BENTUK SILINDER Slamet, Widodo
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The satellite temperature during its orbit has an extreme value. For this reason, we have to predict the temperature of the satellite structure. A satellite designer needs to analyze the structure temperature based on the heat transfers analysis. Two factorsare needed a view factor and a radiation coupling factor. The thermal distribution on a satellite with cylinder structure under extreme illumination of solar radiation will be analyzed upon its three walls: top, mantle, and bottom of the cylinder.
SIMULASI KINERJA SKEA DI KABUPATEN TIMOR TENGAH SELATAN MENGGUNAKAN WAsP Ibrochim, Malik
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The analysis towards the performance of wind turbin simulation has been done in the District of Timor Tengah Selatan, Nusa Tenggara Timur Province by using the method of WAsP simulation. The data used as the simulation input are the wind speedand direction observed in Oelbukbuk vector map of TTS District and 3 (three) brands of 600kW wind turbin. The result shows that the performance of NEG-MICON wind turbine type NM 600-48 brand is better than 2 other brands (Vestas type V44 and Bonus type MKIV) that were simulated based on the wind climate and topography condition at TTS District NTT Province. Based on CF value, NEG-MICON type NM 600-48 wind turbine is 44,27 %, bigger than 2 other brands.
KARAKTERISTIK DINAMIK STRUKTUR ROKET RKN BERTINGKAT PADA KONDISI TERBANG-BEBAS (FREE FLYING) HPS, Sugiarmadji
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Dynamic Characteristic Data of a rocket structure, such as eigenvalues and eigenvectors (mode shapes), are needed to protect the payload components’ safety to the 1st frequency resonance of rocket structures. Here, dynamic characteristic data analysis for the RKN Two-Stages rocket structures will be conducted by using a software based on a Finite Element Methods-FEM. On “free-flying” conditions, normal mode analysis results show that the 1st natural frequency of the RKN rocket from the first up to sixth mode shapes are of ω ≤ 5.56895E-4 Hz. It means that payload components are safe tothe 1st natural frequency of the rocket structures. The 1st natural frequency of rocket structures will give influence to the payload components in lateral and vertical directions at higher than = 134 Hz.

Page 32 of 37 | Total Record : 364

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