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INDONESIA
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 333 Documents
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PENGARUH PENAMBAHAN FILLER SIO2, CARBON BLACK, DAN TIO2 PADA SIFAT MEKANIK LINER EPOKSI POLISULFIDA MOTOR ROKET CASE BONDED (THE EFFECT OF SIO2, CARBON BLACK AND TIO2 FILLER ADDING TO MECHANICAL PROPERTIES OF EPOXY POLYSULFIDE LINER OF CASE BONDED MOTOR ROCKET) Wiwiek Utami Dewi; Bambang Soegiono
Jurnal Teknologi Dirgantara Vol.11 No.1 Juni 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Liner epoksi polisulfida virgin (tanpa filler) tidak cukup kuat untuk menahan beban struktural dan kondisi yang ekstrem selama roket beroperasi oleh karena itu penambahan filler sangat penting dilakukan untuk meningkatkan kekuatan mekanik liner. SiO2, carbon black dan TiO2 telah dipilih sebagai filler untuk memperkuat matriks liner epoksi polisulfida pada motor roket case bonded Lapan. Pengaruh penambahan ketiga filler tersebut pada sifat mekanik liner telah diselidiki dalam penelitian ini. Sembilan jenis komposisi liner telah dibuat dan melalui beberapa proses pengujian sifat mekanik yang meliputi: kekerasan, tegangan tarik maksimum, regangan maksimum, dan kekuatan rekat (liner terhadap logam). Hasil penelitian menunjukkan bahwa nilai kekerasan liner sebanding dengan nilai tegangan tarik maksimum liner dan nilai kekuatan rekat liner terhadap logam sebanding dengan nilai regangan maksimum, sementara itu tegangan tarik maksimum liner memiliki hubungan polinomial dengan regangan maksimumnya. Regangan maksimum tertinggi (52%) dicapai pada nilai tegangan tarik maksimum 16,25 kg/cm2.Kata kunci: Sifat mekanik liner, Epoksi polisulfida, Filler, Case bonded
COMPARATIVE STUDY OF WING LIFT DISTRIBUTION ANALYSIS USING NUMERICAL METHOD Angga Septiyana; Ardian Rizaldi; Kurnia Hidayat; Yusuf Giri Wijaya
Jurnal Teknologi Dirgantara Vol. 18 No.2 Desember 2020
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2020.v18.a3349

Abstract

This research focuses on calculating the force distribution on the wings of the LSU 05-NG aircraft by several numerical methods. Analysis of the force distribution on the wing is important because the wing has a very important role in producing sufficient lift for the aircraft. The numerical methods used to calculate the lift force distribution on the wings are Computational Flow Dynamics (CFD), Lifting Line Theory, Vortex Lattice Method and 3D Panel Method. The numerical methods used will be compared with each other to determine the accuracy and time required to calculate wing lift distribution. Because CFDs produce more accurate estimates, CFD is used as the main comparison for the other three numerical methods. Based on calculations performed, 3D Panel Method has an accuracy that is close to CFD with a shorter time. 3D Panel Method requires 400 while CFD 1210 seconds with results that are not much different. While LLT and VLM have poor accuracy, however, shorter time is needed. Therefore to analyze the distribution of lift force on the wing it is enough to use the 3D Panel Method due to accurate results and shorter computing time.
PERANCANGAN TABUNG MOTOR ROKET RX-150-LPN BERDASARKAN ANALISIS PERHITUNGAN DAN EKSPERIMEN Atik Bintoro
Jurnal Teknologi Dirgantara Vol 1, No.1 Juni(2003)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The rocket motor tube is primary construction of rocket motor, this function is as combustion propellant chamber. The inner pressure will be produced in the tube during the combustion process running and produce structural stress. That's why the tube design is necessary to look the tube endurance of the structural stress. Besides this, the structural weight factor often become constrains, cause the supply of the material structural has light and strength property was limited. Whit concern for the structural stress and the structural weigth, it has been design the tube of RX150-LPN rocket motor, by analysis and experiment method. The analysis method was run affinity by finite element method, and the experiment method affinity by static test of the rocket motor tube. The design has purposed to find the strength and stiffness tube construction and was made the material light relative property. From the design was found characteristic of the product design is in tin of wall= 33mm, inner diameter=15 cm, length of tube=1,4 m, material=alloy steel AISI H11, weigth=17 kg and the prototype has endurance with 35 kg per cm on inner pressure.
SIMULASI GERAK DAN ANALISIS KESTABILAN KOPLING INERSIA WAHANA DIRGANTARA DENGAN BENTUK BADAN RAMPING Hari Muhammad; Hilman Samputra; Yazdi I. Jenie; Javensius Sembiring
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 Inertia coupling is a motion phenomenon of a high-speed airplane having slender body and low aspect ratio. This inertia coupling happens when the aircraft performs a roll manoeuvre motion with a high roll rate. This paper will discuss the derivation of inertia coupling equations of motion, modelling equations of motion in the Matlab/Simulink software, simulating the dynamics motion, and analyzing the stability of the inertia coupling. Numerical simulation and stability analysis of the inertia coupling for a fighter aircraft will be presented in this paper. Keywords:Inertia coupling, Stability analysis, Flight simulation, Slender body
REVIEW VISUALISASI SCHLIEREN PADA TEROWONGAN ANGIN SUPERSONIK Jefri Abner Hamonangan
Jurnal Teknologi Dirgantara Vol. 17 No. 1 Juni 2019
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2019.v17.a2999

Abstract

Terowongan angin merupakan sebuah fasilitas yang mensimulasikan aliran udara dengan berbagai variasi kecepatan pada sebuah benda. Peneliti dan perekayasa menggunakan terowngan angin untuk mengamati dan mengevaluasi perilaku sebuah benda pada kecepatan udara tertentu. Terdapat 2 metode dalam proses pengamatan perilaku benda pada pengujian terowongan angin, yaitu dengan menggunakan balance dan visualisasi dengan menggunakan schlieren.
ANALISIS SISTEM DINAMIKA TERBANG (FLIGHT DYNAMICS) SATELIT LAPAN TUBSAT Abdul Rahman; Agus Nuryanto.; Firman Hartono
Jurnal Teknologi Dirgantara Vol 6, No.1 Juni (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Phase peluncuran dan awal orbit (Launch and Early Orbit Phase – LEOP) merupakan tahapan kritis dalam siklus pengoperasian sebuah satelit. Aktivitas utama dalam phase peluncuran dan awal orbit satelit terdiri dari pelacakan, pengecekan sistem satelit, pengendalian sikap dan pengujian muatan. Dalam makalah ini akan diulas tahapan-tahapan tersebut terkait dengan sistem dinamika terbang (Flight Dynamics) Satelit LAPAN-TUBSAT atau Satelit LAPAN-A1.
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.
Front Pages JTD Vol 15 No 2 Desember 2017 Redaksi Jurnal
Jurnal Teknologi Dirgantara Vol. 15 No. 2 Desember 2017
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2017.v15.a2914

Abstract

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.
PENGUJIAN MODUL PENGOLAH DATA TELEMETRI LAPAN-A3/IPB UNTUK MENGHASILKAN PRODUK LEVEL-0 (THE TESTOF LAPAN-A3/IPB TELEMETRY DATA PROCESSOR MODULE TO PRODUCE LEVEL-0 PRODUCT) . Suhermanto
Jurnal Teknologi Dirgantara Vol. 14 No. 2 Desember 2016
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2510

Abstract

Telemetry data processing modulis a software for converting the LAPAN-A3/IPB telemetry data into raw sensor data (level-0 product). Telemetry data output from the High Data Rate Modulator-demodulator (HDRM) becomes an input for telemetry data processor, which has entered its setup parameter. The objective of the research is to test LAPAN-A3/IPB telemetry data processor implementation. The development and processing of telemetry data have been performed on a desktop computer that are divided into two stages, data decoding and data decomposition.The performance of the software has been tested using eight samples of raw-data, consisted of multi-spectral and camera matrix data obtained before and after the launch of the satellite. The test results showed, there were no missing telemetry data frames and damaged codeword in the process of decoding.Data on missing multi-spectral lines  and data on camera matrix frame lost in the process of decomposition were not found. It was concluded that the overall performance of the test result was that the system used was not able todecode, decompose, display quick-look LISA, or extractcamera matrix data in real-time.To perform as required, the computer performance needed to be increased up to 8 times. From this process, approximately 92% of CPU time were used for decoding and only about 8% were for the decomposition, extraction of data LISA, or extraction of data camera matrix.Improvement attempt by changing the word-size of 32bit processors into 64bit, did not give significant results and was only able to improve the processing speed of 8.1%. Abstrak:Modul pengolah data telemetri adalah softwareuntuk mengubah data telemetri LAPAN-A3/IPB menjadi data sensor yang masih mentah (produk level-0). Data telemetri keluaran dari perangkatHigh Data Rate Modulator-Demodulator (HDRM)menjadi masukan bagi pengolah data telemetri, yang parameter set-upnyatelah dimasukkan. Tujuan penelitian ini adalah untuk menguji implementasi pengolahan data telemetri satelit LAPAN-A3/IPB. Pembangunan dan pengolahan data telemetri telah dilakukan di komputer desktop yang dibagi dalam dua tahap, yaitu pendekodean data dan dekomposisi data. Unjuk kerja software telah diuji menggunakan delapan sampel raw-data, terdiri atas data multi-spektral dan matrik kamera yang diperoleh sebelum dan sesudah peluncuran satelit. Hasil uji memperlihatkan, tidak ditemukan frame data telemetri yang hilang dan codeword yang rusakpada proses pendekodean data. Juga tidak ditemukan data pada larikmulti-spektralyang hilang maupun data pada matrik kamera yang hilang pada proses dekomposisi. Dari uji kinerja secara keseluruhan didapat hasil bahwa sistem yang digunakan tidak mampu melakukan dekoda, dekomposisi, menampilkan quick-lookLISA,atau ekstraksi data matrik kamera secara real-time.Perlupeningkatan kinerja komputer hingga 8 kali lebih baik.Dari proses tersebut, sekitar 92% CPU time dipakai untuk pendekodean data dan hanya sekitar 8% untuk dekomposisi, ekstraksi data LISA,atau ektraksi data matrik kamera. Upaya perbaikan yang dilakukan dengan mengubah word-size prosesor dari 32bit menjadi 64bit hasilnya tidak signifikan dan hanya mampu memperbaiki kecepatan proses 8,1%.

Page 27 of 34 | Total Record : 333

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