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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 8 Documents
 1 
Search results for , issue "Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara" : 8 Documents clear
IMPLEMENTASI STASIUN BUMI TT AND C SATELIT LAPAN-TUBSAT DI BIAK Judianto, Chusnul Tri
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

LAPAN-TUBSAT as a satellite pioner project established by LAPAN finally successfully launched on 10 January 2007. The usage of the main payload of the satellite especially can be used for capturing the surface of the globe. All data are captured by the camera in the video analog format and will be transmitted through s-band frequency in FM video modulation. For controlling the attitude and monitoring the health of the satellite, all data telemetry will be transmitted to the ground station on UHF frequency (437,325 MHz). The space craft control center for LAPAN-TUBSAT satellite has been established in Rumpin Bogor. This station will cover from west part until centre part of Indonesia's archipelago. Rumpin ground station situated on 6.22 Deg South and 106.37 Deg East. For covering entire part of Indonesia, its planed to establish a new ground station in Biak Island PApua at 1.17 Deg South and 136.1 Deg East. Design until implementation of this ground station will be elaborated deeply in this paper. Keywords: LAPAN-TUBSAT, TT and C Ground station.
ANALISIS TEKANAN STATIK ALIRAN DI PERMUKAAN PITOT STATIK TEROWONGAN ANGIN TRANSONIK LAPAN Ariwibowo, Agus; Fitroh, Ahmad Jamaludin; Herdiana, Dana
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Static pressure stream analysis has been done on the surface of pitot static for LAPAN transonic wind tunnel by means of numeric and analytic methods. Static pressure hole is placed at 25 cm behind static pitot leading edge. Numerical analysis result demonstrates that shock wave begins to rise under free stream with velocity of 0.9 march. Shock wave occurs in an area around static pitot leading edge so the stream velocity around static pressure hole almost equal with free stream velocity. There is shock wave that cause decreasing of stream total pressure. By known the total pressure and streamn velocity around static pressure hole then static pressure can be calculated. Mach number in the test section can be known from pressure ratio. Keywords: Static pitot, Shock wave, Static pressure, Transonic.
ANALISIS HASIL PENGUJIAN DAN PREDIKSI TEORITIS AERODINAMIKA ROKET RX 300 Ginting, Salam
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

LAPAN has a supersonic wind tunnel facility which could be used for research of rocket model to get aerodynamics characteristic of the model through testing with various speeds within supersonic range. The research on the RX 300 rocket model has been carried out in the above facility at velocity range of 1,5-3 Mach. Some aerodinamic are obtained from this research. Such as lift drag and moment ceofficients. Aerodynamic coefficient is shown in the curve as a function of Mach and angle of attack. This result will be compared with the theoretical calculation and the result is higher around 5 percent than theory. The approach of Quadrature Multhopp is method use in this analysis. The RX 300 rocket model is equipped with foru flaps at the back part of the rocket as a stabilizer when the rocket is launched. This rocket is designed for being able to carry a payload with dimention of 25 cm diameter and 45 cm length. Keywords: Aerodynamic rocket, Wind tunnel.
KAJIAN AWAL MEKANISME REAKSI ELEKTROLISIS NaCl MENJADI NaClO4 UNTUK MENENTUKAN TAHAPAN REAKSI YANG EFEKTIF DARI PROSES ELEKTROLISIS NaCl Prianto, Bayu
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Ammonium Perchlorate is the oxidizer commonly used in propellant. Ammonium Perchlorate compose from ammonium cation (NH4) and perchlorate anion (ClO4). Perchlorate anion can be synthesized from chloride anion (from NaCl solution) by using electrochemical method. Studying of electrochemical mechanism reaction of perchlorate is very important, because ammonium perchlorate is strategic material. With the knowledge of electrochemical mechanism of perchlorate, we will get information of electrochemical reaction process condition, than can be used to do chemical synthesis in the laboratory. Pre-study the mechanism reactions have done by studying of several reaction models. All model reaction is tested by chemical computation method to find effective and eficient reaction model (represented by reaction energy value) From three tested models, we obtained the 3rd model was the effective and eficient reactions to produce perchlorate. The value of Gibbs free energy reaction for hyphochlorite, 240.190 kcal per mol, and 263.974 kcal per mol respectively. Keywords: Elektrolysis, Ammonium Perchlorate, Gibbs reaction.
RANCANGAN AWAL DAN STRATEGI PENGEMBANGAN RUDAL JELAJAH LAPAN Triharjanto R.H.; Sofyan E.; Riyadi A.; Mariani L.; Putro I. E.
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The paper describes academic exercise of designing a cruise missile for Indonesian Armed Forces. The missile is inteded to deliver 300 kg ordinance to the distance of 1000km. The baseline design yield a vehicle with diameter of 530 mm, total length (with booster) of 4,6 m, and weight of 1300 kg. The vehicle has solid rocket booster and turbojet sustainer engine. The vehicle will have the capacity to fly to the pre-programmed target area autonomously by the use of its GNSS-INS system and horning to their target by the use of its optical target seeker or horning radar. The paper also discusses the strategy to develop the aforementioned missile. The design and the development strategy consider the limitation that Indonesian resources have in method involves capacity survey. The study resulted into missile development steps that grow in size and complexity. The milestones of the development are establishment of test vehicle with diameter of 100 mm for vehicle dynamic survey, test vehicle with diameter of 150 mm to study the deployable wing, handling of turbojet system and autopilot qualification, and test vehicle with diameter of 320 mm for seeker and dummy warhead. Keywords: Prelimenery design, guided missile.
RANCANGAN SISTEM ORIENTASI EKOR TURBIN ANGIN 50 KW Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

A fin orientation system for wind turbine with a maximum capacity of 50 kw has been designed. The fin system is designed with for the yawing motion. The method used is based on the moment equilibrium criteria. Eccentricity distance of 10 cm was selected for the design. The location of the fin control is placed at the connection between the generator and the fin bar. The design procedures a fin bar of 6m, with the fin area of 25 m. The center of the fin force is located at 3 m from the nose. Whereas the fin angle to the center of the turbine axis is 21.9 degrees. Keywords: Wind turbin, fin, oreintation.
METODE KALIBRASI TIME DIFFERENT OF ARRIVAL TDOA UNTUK SISTEM PASSIVE RADAR TRAYEKTORI ROKET Widada, Wahyu; Kliwati, Sri
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Design passive ranging base on radio with Time Different of Arrival TDOA (passive RADAR) have been developed for the application of tracking rocket trajectory. Calibration of the passive RADAR can be done in launching site for obtaining optimal position, however it is also require to be done in laboratory for testing the system algorithm. This article describes the calibration method of time delay calculation in laboratory using antenna cable with various of lengths. We obtain an accurate correlation results between time delay from measurement of oscilloscope and calculation TDOA with cross-correlation method. This method is practical and effective for calibration system in the development of passive RADAR. Keywords: TDOA, Passive RADAR, Trajectory rocket, Calibration method, Cross-correlation.-
EVALUASI UNJUK KERJA SISTEM PROPULSI MOTOR ROKET RX-150-1200 DENGAN MENGGUNAKAN PIRANTI LUNAK PRODUK LAPAN Samosir, Ganda
Indonesian Journal of Aerospace Vol. 5 No. 2 (2007): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The propulsion calculations of the rocket motor RX-150-1200 was done by using the propulsion simulation software developed bya the researchers of the Propulsion Division-LAPAN. The results were compared to that of motor rocket static test to find out the occurary of the motor rocket propulsion system design. Mostly, if there is a difference between those two results are less than 10 percent, we may concluded that the propulsion rocket motor design is correct or pseudo-correct classified, because the deviation obtained in this paper is 1.05 percent only. Keywords: Propulsion, Rocket motor.

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