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Heri Budi Wibowo
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Jurnal Teknologi Dirgantara
Published by Lembaga Penerbangan dan Antariksa Nasional
ISSN : 14128063     EISSN : 25977849     DOI : https://doi.org/10.30536
Core Subject : Science, Engineering,
Aerospace Engineering Chemical Engineering, Chemistry & Bioengineering Computer Science & IT Mechanical Engineering Physics
Jurnal Teknologi Dirgantara (Journal of Aerospace Technology) is an Indonesian accredited scientific publication that covers topics of Rocket, satellite, and aeronautics technology, as well as a spin-off from aerospace technology, such as aerodynamics, astronautics, aerospace structure, power and thermal system of satellites, flight controls. Propulsion and energetic technologies, such as propellant, rocket static-test, thermodynamics of propulsion system. Launch vehicle technology and space operations, such as satellite telecommunication systems, space payloads, and ground station technologies.
Arjuna Subject : Teknik (semua kategori) - Teknik Ruang Angkasa
Articles 8 Documents
 1 
Search results for , issue "Vol 5, No.1 Juni (2007)" : 8 Documents clear
ANALISA AERODINAMIKA KENDALI CANARD ROKET RKX 250 Salam Ginting
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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). Keywords: Canard, Dinamika stabilitas, Statik stabilitas, Static margin, Pusat tekanan aerodinamika, Mach number.
THE COMPARATION OF TWO LAPAN'S PROPELLANTS OF DIFFERENT COMPOSITION Bagus H. Jihad; Tresna P. Soemardi; Dedi Priadi
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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.
RANCANGAN DAN IMPLEMENTASI SISTEM PENERIMA S-BAND DATA VIDEO SATELITE LAPAN-TUBSAT abdul Rahman
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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. Keywords: Video surveillance.
PENGEMBANGAN METODE PENENTUAN KARAKTERISTIK RANCANGAN AWAL ROTOR TURBIN ANGIN Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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.
OPTIMALIZATION OF MICROSTRIP SLOT ARRAY ANTENNAS FOR MULTI-WIDEBAND Iskandar Fitri
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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.
ANALISIS DESAIN, TEKNOLOGI DAN PRESTASI TURBIN ANGIN 10 KW Dines Ginting
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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.
SISTEM KONTROL SUN SEEKER SUATU MODEL UNTUK MENGENDALIKAN PERILAKU WAHANA ANTARIKSA Eko Budi Purwanto
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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
PEMBENTUKAN STRUKTUR MIKRO DAN SIFAT MAGNETIK Sm2Co17 MELALUI CARA SINTERING Mabe Siahaan
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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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. Keywords: Magnet permanen, SmCo, Proses sintering, Struktur mikro, Koersivitas.

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