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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 3, No.2 Desember (2005)" : 7 Documents clear
RANCANGAN DAN ANALISIS STRUKTUR SUDU TURBIN ANGIN LPN 10000 E Sulistyo Atmadi; Firman Hartono
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a816

Abstract

Structure of the LPN 10000 E wind turbine blade has been manufactured and its structural analysis to find out the strenght of this structure during its operation has also been conducted. The method of aero bending moment and centrifugal bending moment and load has been used while neglegting frcitional and torsional load. The analysis is obtained for composite blade strengthened by high strength carbon unidirectional reinforcement composite. With safety factor of 1.3 minimum, it was concluded that the blade is strong enough to use at its designed operational load.
MODELING AND SIMULATION OF PROLATE DUAL-SPIN SATELLITE DYNAMICS IN AN INCLINED ELLIPTICAL ORBIT : CASE STUDY OF PALAPA B2R SATELLITE - J.Muliadi; Said D.Jenie; A Budiyono
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a812

Abstract

In response to the interest to re-use PAlapa B2R satellite nearing its End of Life (EOL) time, an idea to incline the satellite orbit in order to cover a new region has emerged in the recent years. As a prolate dual-spin vehicle, Palapa B2R has to be stabilized against its internal energy dissipation effect. This work is focused on analyzing the dynamics of the reusable satellite in its inclined orbit. The study discusses in particular the stability of the prolate dual-spin satellite in the effect of pertubed field of gravity due to the inclination of its elliptical orbit. Palapa B2R physical data was substituted into the dual-spin's equation of motion. The coefficient of zonal harmonics J2 was induced into the gravity-gradient moment term that affects the satellite attitude. The satellites's motion and attitude were then simulated in the pertubed gravitational field by J2 with the variation of orbit's eccentricity and inclination. The analysis of the satellite dynamics and its stability was conducted for designing control system for the vehicle in its new inclined orbit.
NITROSELULOSA DARI KULIT BATANG PISANG Loekman Satibi
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a817

Abstract

This paper describes the manufacturing of nitrocellulose from the bark of banana tree as a model of the manufacturing from other sources of cellulose in general. The process can be devided into two steps. The fisrt step is the production of cellulose from the bark of banana tree by coustic soda process while in the second step the cellulose obtained then subjected to nitration procces using nitric acid and controlled by addition of sulfuric acid. In the fisrt step dry bark of banana tree digested using coustic soda solution. Coustic soda concentration, the weight ratio of coustic soda solution to dry bark of banana tree, and digestion time were taken as process variables. The results of the fisrt step concludes that the highest cellulose yields is 33,36 percent, obtained at the digestion operating condition of NaOH concentration 3,33 percent, ratio of NaOH solution to dry bark of banana tree 12per1 and digestion time 4,5 hours and permanganate number is 17,27, while the lowest permanganate number of cellulose is 14,40 in accord with almost the lowest yield 26,58 percent obtained at the digestion process condition of NaOH concentration 5 percent, ratio of NaOH solution to dry bark of banana tree 12per1 and digestion time 4,5 hours. These results are almost in accord with the prediction. The second step operation will be accomplished after the completion of the equipments. Sulfuric acid solution is used to control nitration process based on the third Le Chatelier chemical principle.
KONTROLER GAIN SCHEDULING UNTUK RUDAL UDARA KE UDARA Rika Andiarti
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a813

Abstract

A control system for an air-to-air guided missile is developed. Gain scheduling control technique is used to perform the missile flight toward a moving target. The simulation results show that the gain scheduling control technique is effective to obtain the desired missile performance.
KARAKTERISTIK DINAMIKA STRUKTUR SATELIT MIKRO LAPAN-TUBSAT Robertus Heru Trihajanto; - Sugiarmadji HPS
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a814

Abstract

The TUBSAT-LAPAN micro satellite is planned to be launched using PSLV rocket. The design constraints of the mechanical system of the satellite are able to accomodate structural requirment for PSLV, which are first resonance frequency in the rocket longitudinal axis 90 Hz and first resonance frequency in the lateral axis 45 Hz. Therefore, the structural dynamic characteristic data of the satellite is important to be evaluated, such as natural frequency and mode shapes of the satellite structures, The normal modes analysis made is done usingh Finite Element Methods commercial software NASTRAN. To simplify the FEM modeling the satellite components inside the compartmens is replaced by a dummy load simulating their contribution to satellite mass, centerof gravity and inertia, which was made by the same material as the satellite's structure, i.e. Al-Alloy 2024T351. Meanwhile, the FEM modeling for both the UHF antena used the Stainless Steel materials as the real antena. The analysis results show that the lowest local natural frequency of the satellite occurs on the UHF antena. The first natural frequency of the antena structures in lateral direction is 52,29 Hz. The first natural frequency of the satellite in lateral direction 151.47 Hz completing the satellite integration, vibration test was done to the satellite. The test shows that the first global frequency is 72-75 Hz in the lateral direction and 148 Hz in longitudinal direction. Structural dynamic characteristic of TUBSAT_LAPAN micro satellite in free flying condition are also analyzed using no-constraint condition to check the safe separation clearance scenario. The results show that the first natural frequencies for satellite structures (combination) become very small, less than 0.00032 Hz. But, the lowest of the first natural frequency for UHF antena structures is almost constant, 52.30 Hz in lateral direction.
ANALISIS BEBAN TEKUK KRITIS STRUKTUR SANDWICH BAHAN KOMPOSIT PADA SIRIP ROKET RX LAPAN Ronald Gunawan Putra
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a815

Abstract

The using of sandwich structure on the tail of RX LAPAN Rocket offers several advantages compared to conventional structure, such as lightweight, higt stiffiness and good fatigue property. But, one of the problems is its weakness under compressive loads, especially when there is a delaminated area. Buckling modes that often occur in sandwich structure due to compressive loads is overall buckling. This paper will analyze the influence of delamination over critical buckling load with finite element method using 2-D modeling.
PENELITIAN KARAKTERISTIK AERODINAMIKA TRAILING EDGE SIRIP ROKET PADA KECEPATAN TRANSONIK DENGAN SIMULASI NUMERIK Agus Aribowo
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a811

Abstract

Research of fin aerodynamic at a speed of Transonik of importance remember at this speed regim rocket have strongly increas in coefficient of drag, where will cause negativety to attainment of altitude target or its dynamics stability. In general there is 3 fin type which is inverterate to be used by rockets of LAPAN. Third of him have been done by examination use simulation of CFD in 2-D compressible flow at a speed of 1.6 M to 2.4 M. From result of the research discovered behavioral phenomenon born embryo of shockwave at a speed of transonic in region of models B trailing edge cause direct to degradation of pressure and enlarge coefficient of drag.

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