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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 6 Documents
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Search results for , issue "Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara" : 6 Documents clear
RANCANG BANGUN SISTEM PENAHAN PANAS PADA MOTOR ROKET CIGARETTE BURNING Sutrisno
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The thrust of cigarette burning rocket motor is relatively lower but the is burning time is too long than that of the radial burning. The cigarette burning rocket motor structure easy to be fail due to the thermal stress thermal effect. Hence the thermal insulation sistem becomes very important. This paper discuss about the design and preparation of thermal insulation system in the cigarette burning rocket motor. The carbon and polyester fiber were used as the thermal protector materials in burning chamber. The liner matrix and inhibitor in the cap side were made from epoxy. O-ring spacer was applied to avoid the gas leakage from the combustion chamber. The performance of thermal insulation system was tested through static test of rocket motor. The result of the test provide that thermal insulation system showed the good performance. It is found that the burning time of the rocket motor is 116 second and the maximum temperature of the outer surface of the tube is 139 degree celcius.
EFEK DEFLEKSI PADA SUDU TURBIN ANGIN TERHADAP KELUARAN DAYA Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The type of material used in the fabrication of wind turbine blade is a very important factor so that it will not exceed the allowable maximum deflection. An analysis is conducted to study this deflection effect to that power output and as case study, a 7.6 m blade of 10 kW LPN 10000 E turbine is used. Several assumption as such as deflection due to wind speed at perpendicular to local plane local blade are diameter blade and direction of aerodynamic at aerofoil plane local blade are considered. The distribution of blade deflection along the twisted span is assumed uniform. Calculation is performed for the polynomial order of 2,3 and 4, with variety of deflection of 0.2 m, 0.5m, 1 m and 1.5 m. for design wind speed of 9 m per s it was found that for 0.5 deflection, the losses of 6 percent, 9 percent and 12 percent for blade shape polynomial order 2,3 and 4 consequentively are produced; whereas for 1.5 m deflection, losses are 46 percent, 53 percent, and 56 percent for the same polynomial shape. If a maximum loss of 10 percent is taken, then the max allowable deflection is 0.5 m.
SISTEM WIND-DIESEL UNTUK PEMBANGKIT LISTRIK DI LOKASI DENGAN KECEPATAN ANGIN MENENGAH DI INDONESIA Pakpahan, Sahat
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Windspeed is used as a reference in utilization of windturbine as a generating system and will be the main variable for calculation of the energy produced at a certain location. Windspeeds are classified in small scale, medium and large scales. Applications of small scales are generally in the stand-alone mode, while the large systems are intended for interconnection into the utility grid. In between, there are medium scale applications with the annual average windspeed of 4.0 m/s - 50 m/s. Examples of applications are hybrid of windturbine with local diesel generating sets, known as wind-diesel system using one or more windturbines of the size of 10 kW-100 kW and to be matched with the capacity of the existing deisel. most applications are in the intermittent mode of operation in order to obtain higher fuel saving which is used to operate the diesel. Some configurations, selection of components, modelling and calculations are presented to identify more detailed behaviour of the system.
PENGEMBANGAN MODEM AFSK UNTUK TELEMETRI MUATAN ROKET UHF Widada, Wahyu
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Modem is an important component in the telemetry data system of the rocket. The telemetry data based on amateur radio is usually used an AFSK modem. This paper describes the development of AFSK modem using a microcontroller which the speed can be set to the maximum bandwidth of the radio. The prototype is use a 16 MHz of microcontoller and the speed can be set to 2.4 kbps that available to the standard bandwidth of an amateur radio.
PENELITIAN KARAKTERISTIK AERODINAMIKA SAVONIUS BERSUDU BANYAK DENGAN METODA PENGGESERAN MESH Aribowo, Agus
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Rotation of Savonius blades could be simulated using Sliding Mesh methode. The effective solution can be obtained by interfacing between moving zone and fixed zone by coordinating the linked cell. The number of tested blades 2,3,4 and 6. The result is the Savonius turbine with 3 blades having torque coefficient higher and efficiency level the compared which the other blades. The spacing of blade axis make airflow infiltrate and causing increase of force momen and negative drag force. By increasing the number of blades will result in the reduction of negative and positive force between one blade to the other. As a result, the performance will be reduced due to the increased number of blades.
TEKNIK KONTROL SLIDING MODE UNTUK AUTOPILOT ROKET Andiarti, Rika
Indonesian Journal of Aerospace Vol. 4 No. 1 (2006): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper deals with autopilot for rocket tracking problem by using sliding mode controller. Rocket model is considered as a linear system with two control input; wing and tail deflection. Simulation results show that the controller effectively works and gives desired performance (fast reaching and low chattering).

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