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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 11 Documents
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Search results for , issue "Vol. 17 No.2 Desember 2019" : 11 Documents clear
Back Pages JTD Vol 17 No.2 Desember 2019 Redaksi Jurnal
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3284

Abstract

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AnaLISIS KESELAMATAN RADIASI GEDUNG LABORATORIUM RADIOGRAFI PUSTEKROKET LAPAN SECARA TEKNIS DAN LEGAL Rika Suwana Budi
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3208

Abstract

Analisis keamanan radiasi diperlukan untuk mengevaluasi tingkat keamanan radiasi dan tindakan yang diperlukan pada saat bekerja atau berada dilingkungan dengan radiasi tinggi. Hasil pengujian tingkat kebocoran radiasi menunjukkan bahwa gedung laboratorium uji radiasi memerlukan penambahan dinding perisai. Kata kunci:paparan, kebocoran radiasi, perisai radiasi  
PRELIMINARY THERMAL CONTROL DESIGN ANALYSIS OF LAPAN SAR-MICROSATELLITE DEPLOYABLE SOLAR ARRAY PANEL USING ONE NODAL METHODE Poki Agung Budiantoro; Ahmad Fauzi
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3155

Abstract

LAPAN SAR-Microsatellite is the first LAPAN micro satellite being developed and planned to carry a Synthetic Aperture Radar (SAR) payload.  Different from optical satellites that have been developed, LAPAN SAR-Microsatellite requires a lot more power. Solar array panels are needed to generate solar radiation into electrical energy which is used by all of subsystem satellite as energy to turn on and turn off all of components. More larger the area of solar array panel, more greater to the energy obtanied. Therefore, the needed of deployable solar array panel is a must caused by the dimension of the main body structur (MBS) are not large enough. Solar cells will experience a decrease in efficiency if they experience excessive heat. If there is a decrease in efficiency in the solar cell, it will have an impact on the decrease in power produced. The purpose of this study is to conduct thermal design on solar panels to maintain temperature according to their working temperature. Calculations are carried out on the temperature of solar array panel with various optical properties in the upper and lower panel that best which will be use using one nodal analysis methode According to the calculation result from all of the designs passive thermal control system on this study show that Design-5 is the best thermal control design which can be used for LAPAN SAR-microsatellite deployable solar array panel which α=0.24 at the top and ε=0.9 at the bottom surface of solar array panel.
ANALISIS PENENTUAN POWER LOADING PADA DESAIN AWAL PESAWAT TERBANG TANPA AWAK LSU-05 NG Novita Atmasari; Eries Bagita Jayanti; Nur Mufidatul Ula; Mohamad Luthfi Ramadiansyah; Redha Ramadhan Akbar; Prasetyo Ardi Probo Suseno; Ardian Rizaldi; Kurnia Hidayat; Angga Septiyana
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3162

Abstract

Penelitian ini berfokus pada analisa penentuan power loading pada awal desain pesawat LSU-05 NG. Dengan menentukan power loading maka kebutuhan daya engine untuk pesawat LSU-05 NG dapat diestimasi. Artinya pemilihan engine dapat dilakukan sehingga menghasilkan gaya dorong agar pesawat dapat melakukan misi pemantauan dan foto udara dengan baik.  Metode yang digunakan untuk analisa penentuan power loading adalah teknik Matching Chart atau Matching Plot dengan memilih titik optimal dari lima konstrain yaitu jarak take-off, climb rate, stall speed, cruise speed, dan landing. Hasil penelitian menunjukkan bahwa dengan massa 85 kg dan luas sayap 3,22 m2 pesawat LSU-05 NG membutuhkan daya 9.7 hp. Penjelasan lebih detail akan dijabarkan pada bagian selanjutnya.
SISTEM KENDALI KOOPERATIF UAV UNTUK MENDUKUNG PENGAWASAN ILLEGAL FISHING Agus Wiyono; Teuku Muhammad I. Hakim
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3128

Abstract

Terjadinya kegiatan illegal fishing sangat merugikan bagi bangsa Indonesia, terutama bagi para nelayan. Kementerian Kelautan dan Perikanan merupakan institusi pemerintah yang memiliki kewenangan dalam melakukan pengawasan dan penindakan terhadap kegiatan illegal fishing. Salah satu kegiatan pengawasan yang dilakukan selama ini adalah dengan memanfaatkan pesawat terbang berawak. Hal tersebut memiliki beberapa kelemahan. Untuk melengkapi kekurangan yang ada dalam penggunaan pesawat terbang berawak, pengoperasian UAV dapat digunakan untuk mendukung operasi pengawasan illegal fishing. Penggunaan single-UAV tidak akan sesuai tugas pengawasan dimana area yang diawasi sangatlah luas. Aplikasi multi-UAV untuk melaksanakan tugas semacam ini akan cukup efektif. Untuk mewujudkannya suatu system kendali kooperatif telah dibangun. Pada tahap pertama, sistem kendali dibangun dan diuji dalam lingkungan virtual yaitu melalui simulasi. Perangkat lunak yang digunakan untuk membangun system kendali adalah: Matlab/Simulink untuk membangun sistem kendali terbang dan X-Plane 9 digunakan untuk pemodelan matematis pesawat dan visualisasi dinamika pesawat. Metoda kooperatif yang digunakan adalah leader-follower. Hasil yang diperoleh menunjukan bahwa simulasi multi-UAV dengan menggunakan Matlab/Simulink dan X-Plane telah berhasil digunakan untuk mengendalikan 3 UAV mengikuti topologi kooperatif.
Effect Of Rubber Damper Stiffness And Tire Pressure To Reduce Ground Reaction Load Factor On Main Landing Gear Using Multi-Body Simulation (MBS) Rigid Model Dony Hidayat
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3131

Abstract

Landing Gear Drop Test (LGDT) utilizes the apparatus requiring a substantial time and cost. Virtual LGDT (vLGDT) using MSC ADAMS software is one of the solutions for initial stage to testing landing gear. From simulation with vsink 1.7 m/s and load 22000 N obtained contact/impact force that ensue in  MSC ADAMS was 73650 N, while from experimental was 73612 N. The difference between vLGDT and LGDT result is 0.05 %. To obtain ground reaction load factor below 3 in vsink = 3.05 m/s, the rubber damper should have stiffness in the range of 1900 - 2100 N/mm and for the tire pressure of  60 - 65 psi.
VISUALISASI 2 DIMENSI POSISI SATELIT ORBIT RENDAH MENGGUNAKAN SGP4, MERCATOR, DAN VISUAL BASIC 6 Bina Pratomo
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3154

Abstract

Perkiraan posisi satelit sangat diperlukan oleh banyak penggiat satelit untuk dapat mengakses satelit tepat waktu terutama satelit orbit rendah yang posisinya tidak selalu tepat di atas sebuah daerah secara terus menerus, dengan menggunakan data TLE, algoritma SGP4, dan teknik mercator yang di implementasikan ke dalam bahasa pemrograman visual basic 6 berhasil memvisualisasikan posisi satelit dalam tampilan dua dimensi.
LOW COST EMBEDDED CONTROLLER SIMULATION FOR MISSILE IN REAL-TIME ENVIRONMENT Idris Eko Putro; Harry Septanto
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3159

Abstract

This paper focuses on the development of real-time environment for low cost embedded system to control flight performance of missile. Real-time simulation is generated by using xPC target so that standalone target boot can be developed, and target PCs can be simulated in real-time. Two PCs and single board computers (SBCs) are required to configure the host and standalone target respectively. The host PCs are used to control the target PCs while these target PCs run simultaneously in real-time. Target PCs are divided into plant platform and controller platform. Plant platform represents missile dynamics model, while control algorithm is compiled to the other system as controller platform. Linear control synthesis will be implemented for maintaining flight stability of missile using optimal control approach based linear quadratic regulator (LQR). This real-time system should resemble the environment of future flight test.Keywords: r
Front Pages JTD Vol 17 no.2 Desember 2019 Redaksi Jurnal
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3283

Abstract

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Aerodynamic Characteristic Optimization on The Design of Anti - Ship Missile for Indonesian Fast - Attack Boat Fuji Dwiastuty
Jurnal Teknologi Dirgantara Vol. 17 No.2 Desember 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.a3157

Abstract

Missile is one of Indonesia 7 self – reliant main weapon system programs. Therefore research on the anti – surface ship missile system concept had been carried out at the Faculty of Defense Technology, Defense University. This research aims to abtain optimal design of anti – ship missile concept from previous research, i.e. 2 stages cruise missile with diameter of 0.36 m, total length of 5.19 m, cruise flight altitude of 17 m, and cruise flight speed of 0.88 Mach. The optimation is done on the missile’s aerodynamics characteristics to maximize its lift to drag ratio, which is one of the factor that determine the missile’s performance. Variables of nose cone shapes, number of wings, and body cross sections were chosen for evaluation of lift to drag ratio. The research found that nose cone shape did not affect the aerodynamic characteristics since the flight speed is subsonic. From the rest of the variables, it is found that the best configuration is missile with 2 wings with root length of 1.18 m, height of 0.79 m, and tip length of 0.71 m, elliptical body cross section,  and the missile is to be flown at 6o angle of attack.

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