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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. 1 Juni (2010): Jurnal Teknologi Dirgantara" : 9 Documents clear
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.
ALGORITMA PENGENALAN POLA BINTANG UNTUK DETEKSI POSISI BINTANG PADA STAR SENSOR SATELIT LAPAN Saifudin, M. Arif; Triharjanto, Robertus Heru
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Star sensor is a high accuracy sensor for a satellite attitude determination. This sensor identifies the position of stars in celestial map by comparing the position of stars on its active sensor with the star position data contained in its catalogue. An algorithm is needed to recognize the star pattern imaged by sensoring and calculating the position of the stars. An efficient and accurate algorithm is needed to improve the performance of the star sensor for satellite attitude determination. A simple star pattern recognition algorithm uses the neighbourhood technique. The first approach of algorithm is detecting the brightest star and its neigbours in the sensor Field of View (FOV) and identifying whether the stars in image sensor are fit to the star pattern in the catalogue.The simple catalogue used contains the star position and all its neighbouring stars within particular distance in the scope of FOV. Test result showed that neighbours technique has an accuracy below 1 arc min which correspond to the typical accuracy value of star sensor.
SIMULASI DAN PERHITUNGAN SPIN ROKET FOLDED FIN BERDIAMETER 200 mm Fitroh, Ahmad Jamaludin; Saeri
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

One of rocket movement types is spin maneuver. The rocket rotation towards the axisymmetric axis is needed so the rocket can move straight in it’s flight line. The object of spin simulation and calculation in this work is the Rocket of LAPAN with the diameter of 200 mm. The simulation and calculation were done for 0.6, 1.0, 2.0, and 3.0 Mach of flight speed. The simulation and calculation results show that spin anddrag of fin will increase while the flight speed is increasing. The spin and drag of fin for 3.0 Mach of flight speed are 36 rps and 16.6 kg respectively
ANALISIS RADIUS AMAN AKIBAT KEGAGALAN STRUKTUR SUDU SKEA 50 KW PADA SAAT BEROPERASI Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Analysis on the safe radius of a blade structural failure during operation, is studied on this paper. The particular blade under analysis is the SKEA 50 kW LAPAN. The rotor is installed at 18 m height. The analysis is based on the modified straight motion and rotational momentum formulation. The result showed that at the maximum design rotational speed of 80 rpm, the blade would be thrown out of it centre to 73 m horizontally, and 35 m vertically above the ground. On the other hand, the failure at the root of the blade would be thrown and spinned at its centre of mass at the speed of 145 rpm.
PENERAPAN LOW PASS FILTER UNTUK MEMPERBAIKI HASIL ESTIMASI SUDUT PADA SISTEM RADIO TRACKING ROKET Zain, Satria Gunawan; Susanto, Adhi; Widodo, Thomas Sri; Kliwati, Sri; Widada, Wahyu
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Radio tracking system can be applied to track the position of a rocket and is potential to be developed to replace the GPS technology. This system is used to estimate the direction angle (azimuth and elevation) of transmitter source. In measurement and trial there are many noises that cause the results of angle estimation are not accurate. These noises can be obsreved from the value of the angle estimation varied for a fixed measurement point. This is caused by the interference on the received sinyal. This paper discusses the application of low pass filter to eliminate noises in the radio receiver system. Experiment results show that the variation of estimates angle becomes 1600 times smaller compared to the one without filter
PERANCANGAN SISTEM PEREDAM GETARAN PADA MUATAN ROKET RX 320 LAPAN Djatmiko, Agus Budi
Indonesian Journal of Aerospace Vol. 8 No. 1 Juni (2010): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Arising vibration of a rocket while flying may cause a damage at electronic equipments, so that the rocket needs to be tested on what extent does the electronic equipment can receive a vibration. Based on the experience during the roll-out of rocket, a GPS (Global of Positioning System) equipment was found out to experience some disturbance as the rocket suffered acceleration , so that it will be difficult to trace the existence of the rocket. To alleviate a vibrating damper systems, we design a GPS for the rocket of RX 320 – LAPAN which is capable to receive the vibration up to 15 g. The result of scheme by comparising two successive amplitudes of X1 / X2 = 1 / 02, spring of stiffness k = 12000 N/m and mass GPS m = 0,3 kg with an acceleration of 15 g, gives the damping coefficient c = 24 N/m/second and resonance amplitude X = 9.2 mm

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