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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 7 Documents
 1 
Search results for , issue "Vol 4, No.2 Desember (2006)" : 7 Documents clear
RANCANG BANGUN GENERATOR TURBIN ANGIN TIPE AKSIAL KAPASITAS 200 W Agus Nurtjahjomulyo
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Generator is the component of wind turbine that convert mechanical to electrical energy and has a specific character which operates at low speed rotation ( 1000 rpm). Engineering design of wind turbine generator capacity 200 W discussed in this paper represents the results of fabrication and testing of the generator as a model. The experiment showed that the generator can be producing power 200 W at rotation 450 rpm with torque about 8.5 Nm. Keywords: Generator, Turbin angin.
SISTEM KENDALI ROKET UNTUK GERAK UNPITCHING Rika Andiarti; Edi Sofyan
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

A missile control system utilizing Proportional-Integral-Derivative (PID) controller is proposed. With this controller, the missile is constrained to flight with zero pitch angle. By choosing LAPAN's missile RKX-100 as a dynamic model, this PID controller is applied. Simulation results show that the applying controller seems to be effective in missile unpitching manuver. Keywords : PID Controller, Missile, Unpitching
PERANCANGAN IGNITER UNTUK MOTOR ROKET PADAT RX 420/4000 Sukandi Nasir Rohili
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Igniter is a rocket component with the function of providing activated energy to the surface of solid propellant in the burning chamber of the rocket motor. Igniter design needs overall data of the rocket especially initial free volume and stable combustion pressure of the propellant. The properties of either primer or main charge especially its density and fraction of condensed particles of it combustion products are also needed. This paper presents the design of igniter for RX-420/4000 solid rocket with wagon wheel-cylinder dual configuration. The design result gives data as follows main case length = 302.6 mm, diameter = 52 mm; main charge weight of 338.31 g; volume = 212.19 cc and nozzle throat area = 12.6 mm; the intermediate case of 200 mm length; 30 mm diameter with black powder weight = 310.87 g and volume of 141.37 cc, the overall length of igniter included stick of 402.6 mm. Keywords: Igniter, Motor roket, RX 420/4000.
DESAIN DAN PENGUJIAN STRUKTUR SATELIT MIKRO LAPAN-TUBSAT Robertus Heru Triharjanto
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The paper discuss about the design and test of the structure of LAPAN-TUBSAT micro-satellite, which is the task done by the writer during his time as the member of LAPAN-TUBSAT integration and test. The discussion includes the design requirment for the structure as mechanical interface and its implementation as well as its design validataion process via test as accordance to the requirement set by the launcher authority. Keywords: Satelit mikro LAPAN-TUBSAT.
RANCANG BANGUN PROTOTIPE SISTEM HEADING AUTOPILOT BERBASIS RATE-GYROSCOPE DAN MICROCONTROLLER Wahyu Widada
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

This paper discusses an experiment result of the prototype system feedback control for vehicle heading autopilot. The heading angle is measured with a rate-gyroscope and controlling with a control system based on a microcontroller and a stepper motor. This system is successfully realized within 0.5 degree of the error for heading angle. The accuracy of heading sensor is decrease due to vibration from stepper motor. To overcome such problem we recommended to use an analog lowpass filter and a mounting anti vibration. Keywords: Heading autopilot, Rate-gyroscope, Stepper motor, AVR microcontroller.
SIMULASI PENGUJIAN PRESTASI SUDU TURBIN ANGIN Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Identification of whether aerodynamic performances of a rotor blades has met the criteria according to its design or not, the general procedure is to fabricate and perform a field testing; or testing its model in a windtunnel. Both method require high cost however; therefore, a simulation method using Fluent software had used for obtaining lower cost. The model used in an LS (1)-0417 Mod airfoil having 3 blades and rotor diameter 7.21 m. Simulation test shows a good result with a difference of 4.61 percent for torque and power from design result. Keywords: Sud, Turbin angin, Fluent.
PENGARUH VARIASI SUDUT SERANG SUDU PADA PRESTASI TURBIN ANGIN Sulistyo Atmadi; Ahmad Jamaludin Fitroh; Firman Hartono
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Research on variations of angle of attack turbine blade has been conducted to investigate their correlation with windturbine performances, and for these purposes, AEROFOIL LS (1)-0417 MOD has been selected with 4 angle variations. The first variation is selscted with constant slipstream, the second with Cl max of 0.3, while the third and fouth variations with Cl max of 0.5 and 0.7 respectively. Based on blade element and momentum theory for obtaining efficiency, the following results for all the four variations are 18.15 percent, 16.46 percent, 16.15 percent and 16.26 percent. Hence, it can be concluded that, a highest efficiency is obtained with a constant slipstream as in case 1. In practice, to achieve such configuration, a more accurate blade fabricantion process is required to obtain the highest efficiency. Keywords: Sudu, Sudut serang.

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