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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
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Search results for , issue "Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)" : 8 Documents clear
THE COMPARATION OF TWO LAPAN'S PROPELLANTS OF DIFFERENT COMPOSITION Jihad, Bagus H.; Soemardi, Tresna P.; Priadi, Dedi
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

This paper compares two LAPAN'S propellant compositions. The A propellant has a composition of AP/AL/Binder with ratio of 70/10/20, and propellant B has ratio 75/7.5/17.5, both with HTPB base but different curing agent. As comparator of this simulation is RX-1512.01 rocket that has flight tested. The performances which compared are specific impulse and efficiency characteristic. Result shows that the propellant B gives higher specific impulse, however higher losses is, about 5.373 percent. One to be considered is that the propellant B produce combustion temperature higher than propellant A by 200 k, that may influence the rocket structures. Keywords: Impuls specific, characteristic efficiency, propellant, simulation.
OPTIMALIZATION OF MICROSTRIP SLOT ARRAY ANTENNAS FOR MULTI-WIDEBAND Fitri, Iskandar
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

Microstrip slot antenna fed by matching network of microstrip line to increase very wide-bandwidth and multiband is proposed. The microstrip line composed of multi tuning stubs is used to control slots antenna real impedance to match with impwdance cahracteristic of feeding line so that it could increase the bandwidth. The design are achieves good input impedance in the ranges frequency of 1.3 - 5.1 GHz for single slot and 1.1 - 6.4 GHz for two slots. The bandwidths of antennas become very wide if the slots made in array configuration. The measured return loss S11 agrees well with the simulation results for single slot as axample. Keywords: microstrip slot antenna, array configuration, network impedance, multi tuning stub.
SISTEM KONTROL SUN SEEKER SUATU MODEL UNTUK MENGENDALIKAN PERILAKU WAHANA ANTARIKSA Purwanto, Eko Budi
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

Sun seeker control system doing by monitoring the sun as main reference. The result of monitoring the sun position used for the line correction of space vehicle. In these paper used simulation method for gated parameter value control system. To know the influence of sun seeker control system, simulation was doing with and without lead compensator. The result of simulation show that without sun seeker control system the time settling is ts = 0.35 second and maximum overshoot Mp = 44,4 percent. These results not reasonable for controling of plan with high velocity like rocket and satellite. Later simulation with phase lead sun seeker control system, give settling time ts = 0,12 second and maximum overshoot Mp 5 percent. From the simulation data that sun seeker control system can used for space vehicle control and agree with steady state error specification.Keywords: Sun seeker control system, FFase lead, Waktu penetapan, lewatan maksimum, kondisi tunak
PENGEMBANGAN METODE PENENTUAN KARAKTERISTIK RANCANGAN AWAL ROTOR TURBIN ANGIN Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

A method for determining design characteristics of a wind turbine rotor has been developed. Given the desired power and operational wind speed, the approximate design diameter and rotor rpm can then be determined. The size of the rotor diameter is governed by the blade performance, in which is normally given as power coefficient Cp; designed rotor spedd can be known after calculating the tip spedd ratio. Using this method, the blade and rotor characteristics can be designed quickly as a preliminary design parameter. Keywords: Rancangan awal, Koefisien daya, Tip speed ratio.
ANALISIS DESAIN, TEKNOLOGI DAN PRESTASI TURBIN ANGIN 10 KW Ginting, Dines
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

Small-scale wind energy conversion systems have been developed and utilized for rural electric generation. Performance and success of the systems strongly depend on available wind power as well as the design and technologies. Recently, that alternative energy technology is more important to support the electric supply and to anticipate continously increase of electric needs. In order to increase the use of that renewable energy technology, a 10 kW wind turbine has been chosen to be developed. Analysis of the wind turbine shows that the design, technologies, and performances are specific and limited to the application and wind power availability. The adaption and improvement is needed for developing the more effective use to the wind turbine. Keywords: Wind energy, energy terbarukan, Turbine angin.
PEMBENTUKAN STRUKTUR MIKRO DAN SIFAT MAGNETIK Sm2Co17 MELALUI CARA SINTERING Siahaan, Mabe
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

The studies, observation of microstructure and magnetic coercivity of the permanent magnet sample have been done through a metallurgy powders technique preparation process. The raw materials with the composition of Sm (Co, Cu, Fe, Zr)z equal 8.5 (at percent) initially in the form of powders alloys with the mean particle size of was 20-30 um. This powder is compacted through one direction pressed in the dies and the following with heat treatment steps. After sintering steps and homogeneity of each at a temperatures of 1190 degree celcius and 1130 degree celcius, the solid sample achieved with Sm2Co17 is mainly the magnetics phase. Further heat treatment that their received the next 10 degree celcius/minute until room temperature. And have succeeded to form cellular structures on the matrixs of magnetics phases while other phases in the form cellular structures on the matrixs of magnetics phases while other phases in the form of grain boundary and the magnetics coercivity. Conclution from result of this study is compared with the result of former research.
ANALISA AERODINAMIKA KENDALI CANARD ROKET RKX 250 Ginting, Salam
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

In the framework of guided missile development in LAPAN, Center of Technology has been rocket designed, constructed and then performed a guided missile trial launching in Pameungpeuk in May 2002. However the result was still far from expectation. It has been realized that numerous of factors played a part in the failure of the missile trial launching, which are structure strenght, propulsion, propellant, guidance system and aerodynamic stability. From all the above factors, aerodynamic static stability is the initial requirement which has to be validated before stepping to the next design process. Based on the above situation, it has been carried out a analysis un RKX 250 rocket aerodynamic static stability with canard guidance which configuration is almost similiar with the one that was launched in Pameungpeuk. To find out the rocket's aerodynamic static stability, a research on lift coefficient and drag coefficient must be done first. From the lift coefficient data, a conduction the center pressure of aerodynamics rocket. Method that is used in this research is the ine which was developed by quadrature multhopp which is analytical method (Krasnov N.F.1978).
RANCANGAN DAN IMPLEMENTASI SISTEM PENERIMA S-BAND DATA VIDEO SATELITE LAPAN-TUBSAT Rahman, Abdul
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Abstract

One of the LAPAN-TUBSAT satellite mission is video surveillance. This mission is done with transmiting real time video from satellite. For reception of this transmission in ground station it is needed to specify the specification and general design of the receiver, so that it could receive and process the signal transmission from the satellite to become real time video, Specifying of the specification of this receiver used link budget calculation, transmission type and other RF parameters. The specification and general design of this receiver was implemented as an S-BAnd Video Receiver and already tested using real time transmission from DLR-TUBSAT satellite's video and applied in LAPAN-TUBSAT data reception.

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