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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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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.
Full Pages JTD Vol 15 No 1 Juni 2017 Redaksi Jurnal
Jurnal Teknologi Dirgantara Vol. 15 No. 1 Juni 2017
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Full Pages JTD Vol 15 No 1 Juni 2017
PENGARUH BENTUK DAN KEMURNIAN AL POWDER TIDAK BULAT TERHADAP KINERJA PROPELAN (THE EFFECTS OF UNSPHERICAL ALUMINUM POWDER SHAPE AND PURITY TO THE PROPELLANT PERFORMANCE) Kendra Hartaya; Luthfia Hajar Abdillah; Retno Ardianingsih
Jurnal Teknologi Dirgantara Vol. 11 No.2 Desember 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Telah dilakukan pemilihan jenis aluminium powder yang tersedia di dalam negeri sebagai sumber energi termal dalam propelan. Pemilihan dilakukan dengan harapan bisa menggantikan Al powder yang selama ini digunakan Lapan dalam pengembangan propelan. Pemakaian Al powder jenis lain diharapkan bisa menaikkan impuls spesifik propelan Lapan. Pemilihan jenis Al dilakukan dengan mempertimbangkan kemurnian, bentuk dan ukuran. Untuk mengetahui kemurnian dilakukan uji dengan Atomic Absorption Spectroscopy (AAS) yang ada di Lab Kimia Analitik UGM. Sedangkan untuk mengetahui bentuk dan ukuran Al dilakukan uji dengan Scanning Electron Microscopy (SEM) yang ada di Lembaga Penelitian dan Pengujian Terpadu (LPPT) UGM. Agar Isp propelan bisa meningkat, maka Al dipilih sedemikian rupa sehingga kekeroposan propelan sekecil mungkin dan muatan kedalam propelan sebanyak mungkin. Untuk itu diinginkan Al yang berbentuk bulat dan ukuran kecil dan kemurniannya tinggi. Dari 4 sampel yaitu AlLpn, AlDhn, AlPnc, AlPct, maka AlLpn memiliki kemurnian 89,6% sedikit di bawah AlPnc yang tertinggi 91,7% dan AlLpn memiliki bentuk relatif bulat dibanding yang lain dan memiliki ukuran paling kecil. Keempat sampel Al powder menunjukkan bentuk tidak bulat. Oleh sebab itu disimpulkan bahwa AlLpn (Aluminium yang digunakan Lapan selama ini) adalah relatif paling baik. Aplikasi dalam propelan dengan komposisi yang sama menunjukkan bahwa Isp propelan dengan AlLpn menghasilkan Isp 170-179 detik. Isp ini memiliki rentang 8,75 detik atau 4,5 detik (5%) disekitar nilai tengah (rata-rata). Toleransi 5% dalam nilai Isp ini adalah yang paling kecil dibanding Isp propelan dengan aplikasi ke-3 jenis Aluminium lainnya. Kata kunci : Propelan, Aluminium powder, Isp, Kemurnian, Bentuk
RANCANGAN AWAL SISTEM KOMUNIKASI SATELIT IMAGE PROCESSING LAPAN-TUBSAT Minto Suwarjo
Jurnal Teknologi Dirgantara Vol 1, No.2 Desember(2003)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2003.v1.a782

Abstract

The LAPAN-TUBSAT is a joint reseaverd between LAPAN and TECHNICAL UNIVERSITY OF BERLIN for image processing application. The satellite will be built in with half-duplex transmission system, with uplink frequency is uHF-band 435.075 Mhz in minimum data rate 1200 pbs, while the downlink frequency is S-band 2.2 GHz use data rate 38400 bps. The uplink frequency will functioned for command and donwlink frequencies for telemetry data and image data. The main communication payload consists of transmitter and antenna s-band, tranceiver and antenna UHF-band, two cameras with resolution 50 mm and 1000 mm with PAL standard, data and video multiplexes, on borad data handling and power control unit. The ground station consists of TT and C operates in UHF-band and ground receiver processing operates in S-band frequency. The minimum image signal quality received is 45 dB for BER 10.
MULTI FREKUENSI ENCODER FLIGHT TERMINATION SYSTEM (MULTI FREQUNECY ENCODER FLIGHT TERMINATION SYSTEM) Effendi Dodi Arisandi
Jurnal Teknologi Dirgantara Vol.13 No. 1 Juni 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Flight Termination System (FTS) adalah suatu sistem yang digunakan untuk menghentikan suatu misi peluncuran wahana udara apabila wahana tersebut mengalami kegagalan dalam misinya. Encoder FTS adalah bagian dari FTS yang akan memberikan sinyal perintah dalam bentuk gelombang sinus dengan frekuensi tertentu. Sinyal sinus yang secara umum disebut sinyal tone ranging dapat dibangkitkan dalam rentang frekuensi audio, 20Hz-20KHz. Metode Direct Digital Synthesis (DDS) dapat digunakan untuk membangkitkan sinyal tone ranging yang berupa sinyal sinus atau kotak (pulse). Kerahasiaan sinyal tone ranging yang dikirimkan pada bagian penerima FTS sangat penting agar tidak bisa diganggu oleh sinyal lain. Dengan menggunakan metode DDS AD9850, dapat dihasilkan sinyal sinus multi frekuensi pada endcoder FTS; 750Hz, 1000Hz, dan 1250Hz.Kata kunci: Multi Frekuensi, Encoder FTS, Metode DDS, Penjumlahan Frekuensi
KRISTALISASI AMMONIUM PERKLORAT (AP) DENGAN SISTEM PENDINGINAN TERKONTROL UNTUK MENGHASILKAN KRISTAL BERBENTUK BULAT Anita Pinalia
Jurnal Teknologi Dirgantara Vol 9, No. 2 Desember (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

AP is the solid particles with the largest composition in compossite propellant, with fractions 60-80%. Rounded particles of AP indirectly gives better performance of propellant. Therefore we need experiment the crystallization process to produce rounded AP crystal. In this experiment, crystallization was conducted by using a controlled cooling system. Cooling is done through two stages and using a different coolant. The first stage of slow cooling using water (30°C), and continued rapid cooling with ethylene glycol (-27°C). These experiment generate 45.45 kg AP with a purity 99.67%, 40 mesh crystal size, crystal shape close to round, yield 39.71%. Keywords: Ammonium perchlorate, Crystallization, Rounded crystal
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.
PENENTUAN SIKAP SATELIT BERDASARKAN DISTRIBUSI ARUS LISTRIK PADA PANEL SURYA SATELIT LAPAN-TUBSAT Abdul Rahman; M Mukhayadi
Jurnal Teknologi Dirgantara Vol 7, No.1 Juni (2009)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Pada tanggal 10 Januari 2009 LAPAN telah mengoperasikan satelit LAPANTUBSAT selama dua tahun. Pada tahun kedua pengoperasian satelit ini, star sensor, salah satu sensor kendali sikap mengalami kegagalan. Beberapa prosedur dan metode baru dilakukan untuk melanjutkan misi satelit dalam pengamatan permukaan bumi. Salah satu metode yang digunakan adalah menggunakan panel surya untuk menentukan orientasi sikap satelit. Panel-panel surya tersebut terpasang pada setiap sisi satelit. Sikap satelit kemudian ditentukan berdasarkan perbandingan distribusi arus listrik dari semua panel surya. Setelah orientasi satelit diketahui, operator dapat mengendalikan satelit agar mengarah ke target. Dengan memanfaatkan cara ini, LAPAN-TUBSAT masih mampu menghasilkan data video dengan baik.
SISTEM WIND-DIESEL UNTUK PEMBANGKIT LISTRIK DI LOKASI DENGAN KECEPATAN ANGIN MENENGAH DI INDONESIA Sahat Pakpahan
Jurnal Teknologi Dirgantara Vol 4, No.1 Juni (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Windspeed is used as a reference in utilization of windturbine as a generating system and will be the main variable for calculation of the energy produced at a certain location. Windspeeds are classified in small scale, medium and large scales. Applications of small scales are generally in the stand-alone mode, while the large systems are intended for interconnection into the utility grid. In between, there are medium scale applications with the annual average windspeed of 4.0 m/s - 50 m/s. Examples of applications are hybrid of windturbine with local diesel generating sets, known as wind-diesel system using one or more windturbines of the size of 10 kW-100 kW and to be matched with the capacity of the existing deisel. most applications are in the intermittent mode of operation in order to obtain higher fuel saving which is used to operate the diesel. Some configurations, selection of components, modelling and calculations are presented to identify more detailed behaviour of the system. Keywords: Angin-diesel, Modus bergantian, Penghematan bahan bakar.
PICO-SATELLITE DETUMBLING SIMULATION USING MAGNETIC ATITUDE ACTUATOR (SIMULASI DETUMBLING PADA SATELIT PIKO MENGGUNAKAN AKTUATOR SIKAP MAGNETIK) Ali Muksin; Ridanto Eko Poetro; Robertus Heru Triharjanto
Jurnal Teknologi Dirgantara Vol. 15 No. 1 Juni 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.a2524

Abstract

One of the methods to control Nano/pico-satellite’s attitude is using magneto-torquers as attitude actuators. ITB, at the moment is planning to develop a cubesat. Therefore, the objective of the research was to investigate the performance of such attitude control system for 3U class cubesat. The research used Matlab/simulink-based satellite simulator developed by LAPAN and ITB, and B-dot control law. The advantages of the method are that the actuators are small and lighter compared to the other type of actuators, such as momentum wheels or reaction wheels. However, the disadvantages is that the torques can be created only when the actuator oriented at non-zero angle with local magnetic field. The results showed that the attitude control system could performed the detumbling operation, with the best transient time at about two orbits period. Varying the gain parameter in the controller may result into variation of transient time and even unstability.   AbstrakSalah satu cara untuk mengendalikan sikap satelit nano/piko adalah dengan menggunakan magneto-torquer sebagai aktuator. Saat ini ITB tengah mewacanakan pengembangan cubesat, sehinggga tujuan dari penelitian ini adalah untuk mengevaluasi kinerja sistem kendali sikap berdasarkan medan magnet Bumi pada cubesat kelas 3U. Penelitian ini menggunakan simulator satelit berbasis MATLAB/simulink yang dikembangkan oleh LAPAN dan ITB, moda kendalinya berbasis hukum kendali b-dot. Keuntungan dari sistem kendali ini adalah ukuran dan beratnya yang kecil, dibandingkan dengan moda kendali lain, seperti momentum wheel atau reaction wheel. Sementara kerugiannya adalah hanya bisa menghasilkan torsi saat aktuator mempunyai sudut tidak nol dengan medan magnet Bumi. Hasil menunjukkan bahwa moda kendali tersebut dapat melakukan manuver de-tumbling, dengan waktu transient terbaik mendekati dua periode orbit. Juga ditunjukkan bahwa variasi waktu transient dan ketidakstabilan dapat diperoleh dengan memvariasikan parameter gain pada kontroler. 

Page 26 of 34 | Total Record : 333

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