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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 333 Documents
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PENELITIAN KARAKTERISTIK AERODINAMIKA AEROFOIL SUDU SKEA NELAYAN NILA 80 Sulistyo Atmadi
Jurnal Teknologi Dirgantara Vol 2, No.1 Juni (2004)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2004.v2.a792

Abstract

An economical electric-small-scale wind turbine is intended for an alternative source of energy for fishermans. For the power requirment of wind turbine with the wind condition in Indonesia, an aerofoil research is needed, in particular for the case of SKEA Nelayan Nila 80, with unknown aerofoil data. The focus of the research concentrated on finding aerodynamics characteristic Cl, Cd and Cm for angle of attack regime from 4 to 16 degrees. The result would be used in the modification of existing wind turbine. With limited engineering data, several integrated softwares had been used such as AutoCad 2004, Gambit and fluent 5.2.1 AutoCad was used to digitise aerofoil geometry, gambit was used for grid generation wich then fed into Fluent 5.2.1. for load analysis. The result was quite similiar to N-60 which gives stall angle at around 13 degree-15 degree and Cl per Cd maximum equal 16.
PENGARUH DARI POSISI PUSAT MASSA ROKET YANG TIDAK TERLETAK PADA SUMBU AXIS SIMETRI TERHADAP DINAMIKA TERBANG ROKET BALISTIK (THE DYNAMIC OF THE ROCKET DUE TO THE OFFSET OF ITS CENTER OF MASS RELATIVE TO THE SYMMETRIC AXIS) Ahmad Riyadl
Jurnal Teknologi Dirgantara Vol. 13 No. 2 Desember 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Dalam uji terbang roket balistik kadang terjadi suatu gerakan wobbling yaitu suatu gerakan yang tidak linear menbentuk lintasan yang konus. Fenomena ini dapat terjadi dikarenakan berbagai sebab, dimana salah satu penyebabnya adalah posisi pusat massa roket yang tidak terletak pada sumbu axis simetri roket. Sehubungan roket LAPAN pada umumnya termasuk roket balistik maka perlu dilakukan penelitian untuk mengetahui kemungkinan dapat terjadinya gerakan wobbling pada saat uji terbang yang disebabkan oleh posisi pusat massa roket yang tidak terletak pada sumbu axis simetri. Dari hasil perhitungan pada penelitian ini terlihat bahwa posisi pusat massa roket yang tidak terletak pada sumbu axis simetri roket menyebabkan terjadinya gangguan momen roll, pitch dan yaw pada roket, dimana gangguan dari momen roll, pitch dan yaw tersebut memicu gerakan wobbling.Kata kunci: Pusat massa roket, Simulasi dinamik, Wobbling
ANALISIS POTENSI STASIUN BUMI SATELIT LAPAN-TUBSAT KOTOTABANG UNTUK PENGAWASAN JALUR STRATEGIS SELAT MALAKA (THE POTENTIAL ANALYSIS OF LAPAN-TUBSAT SATELLITE GROUND STATION (KOTOTABANG) FOR OBSERVING THE STRATEGIC CHANNEL OF MALACCA STRAIT) Chusnul Tri Judianto
Jurnal Teknologi Dirgantara Vol 10 No.1 Juni 2012
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

LAPAN-TUBSAT is the first generation of LAPAN satellite program which is developed by technology collaboration between LAPAN and TU Berlin, German. As a surveillance satellite, LAPAN-TUBSAT has ability to observe the earth surface until 5 meter ground resolution by using analog video camera. Utilization of this satellite to observe the strategic location entire Indonesia in real time has not been done thoroughly. Therefore the technical upgrading of the Ground Station in strategic areas such as border areas, the National/International cruise line and National vital objects should be improved. One of the strategic areas of Indonesia is the region of Malacca Strait which is the area of International shipping waterway and border of 4 countries; Indonesia, Malaysia, Singapura and Thailand. Until now, to observe the Malacca region was performed using Rancabungur/Rumpin ground station that have minimum coverage area. The Kototabang ground station is one of the strategic ground stations that cover the entire of Malacca regions which needs to be improved in maintenance and technical operation level. The potential value of Kototabang ground station will be elaborated technically in this paper. Keywords: Kototabang ground station, LAPAN-TUBSAT
Pemilihan Airfoil Pesawat Terbang Tanpa Awak LSU-05 NG dengan Menggunakan Analytical Hierarchy Process Kurnia Hidayat; Ardian Rizaldi; Angga Septiyana; Mohamad Luthfi Ramadiansyah; Redha Akbar Ramadhan; Prasetyo Ardi Probo Suseno; Novita Atmasari; Eries Bagita Jayanti; Taufiq Satrio Nurtiasto
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.a3161

Abstract

Pada perancangan pesawat terbang tanpa awak, pemilihan airfoil sangat penting untuk meningkatkan performa pesawat. Airfoil dipilih berdasarkan karakteristik geometri dan performa aerodinamikanya. Penelitian ini membahas tentang pemilihan airfoil dengan banyak kriteria berdasarkan karakteristik masing-masing airfoil. Pada tahap awal, sebanyak 1504 airfoil tersaring menjadi 5 airfoil terpilih. Airfoil tersebut dianalisis berdasarkan 7 kriteria utama, yaitu Camber, Thickness, Manufacturability, Max C_L, C_(L_0 ), Max C_L angle, dan Max L/D. Berdasarkan analisis tersebut, FX 76-MP-160 terpilih sebagai airfoil terbaik untuk pesawat terbang tanpa awak yang dirancang.
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.
PREDIKSI KEKUATAN STRUKTUR ALAT UJI GETARAN ENGINE LSU SERIES MENGGUNAKAN METODE ELEMEN HINGGA (STRENGTH PREDICTION OF THE ENGINE VIBRATION TEST STAND OF LSU SERIES USING FINITE ELEMENT METHOD) Fajar Ari Wandono; Agus Harno Nurdin Syah
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.a2505

Abstract

In order to know about vibration characteristics of a combination between engine and propeller used in LAPAN Surveillance UAV (LSU) series, it needs a test apparatus called the engine vibration test stand. The engine vibration test stand structure must be strong and stiff to get good result in engine vibration test. In the initial phase, the engine vibration test stand was madeof 1 meter length of ASTM A36 material with H shape and the lower part of it was bolted to the reinforced floor. By using a finite element method software and inputting some parameters from engine DA-170 and mechanical properties of ASTM A36, the engine vibration test stand had safety factor of 26,24. Furthermore, the top five natural frequencies were 61,94Hz, 77,18Hz, 93,79 Hz, 212,23Hz and 286,24Hz.   AbstrakUntuk mengetahui karakteristik getaran dari kombinasi engine dan propeller yang digunakan pada LAPAN Surveillance UAV (LSU) series maka diperlukan sebuah alat uji yang disebut alat uji getaran engine (AUGE). Struktur AUGE harus dibuat kuat dan kaku untuk mendapatkan hasil uji getaran engine yang baik. Sebagai langkah awal telah dibuat sebuah AUGE yang terbuat dari material ASTM A36 yang berbentuk H setinggi 1 meter dengan bagian bawahnya dibaut ke sebuah lantai yang sudah diperkuat. Dengan menggunakan software metode elemen hingga dan memasukkan parameter engine DA-170 serta sifat mekanik ASTM A36 didapatkan bahwa struktur AUGE tersebut memiliki nilai faktor keamanan sebesar 26,24. Adapun lima nilai pertama frekuensi pribadi dari struktur tersebut adalah 61,94 Hz, 77,18 Hz, 93,79 Hz, 212,23 Hz dan 286,24 Hz. 
PENGUKURAN KARAKTERISTIK DINAMIKA STRUKTUR SATELIT LAPAN-ORARI/A2 (STRUCTURAL DYNAMICS CHARACTERITICS MEASUREMENT OF LAPAN-ORARI/A2 SATELLITE) Mohammad Farid Huzain; Robertus Heru Triharjanto
Jurnal Teknologi Dirgantara Vol. 11 No.2 Desember 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Satelit LAPAN-ORARI/A2 merupakan satelit generasi kedua setelah satelit LAPAN-A1 (atau lebih dikenal dengan LAPAN-TUBSAT). Satelit LAPAN-ORARI/A2 ini adalah satelit mikro pertama yang dirancang, dibangun, dan diuji di Indonesia. Makalah ini membahas mengenai pengujian struktur satelit mikro LAPAN-ORARI/A2, dalam hal ini pengujian getar untuk mencari frekuensi natural pertama satelit pada tiap sumbu. Pengujian getar sangat perlu dilakukan untuk memastikan bahwa satelit mampu menerima beban sebagai akibat dari sistem aerodinamik dan propulsi dari wahana peluncur (roket). Pengujian getar merupakan salah satu syarat yang harus dilalui sebelum satelit diluncurkan. Beban pengujian ini mengikuti beban yang dipersyaratkan oleh otoritas peluncur satelit, dalam hal ini ISRO-INDIA, yaitu dengan frekuensi resonansi di atas 45 Hz untuk arah lateral dan di atas 90 Hz untuk arah longitudinal. Hasil pengujian getar satelit LAPAN-ORARI/A2 menunjukkan frekuensi natural pertama arah lateral terjadi pada sumbu-Z pada 97 Hz dan pada sumbu-X pada 73 Hz, sedangkan pada arah longitudinal terjadi pada 162 Hz (sumbu Y/vertikal satelit). Dari hasil pengujian tersebut menunjukkan bahwa satelit LAPAN-ORARI/A2 mampu menerima beban sesuai dengan yang dipersyaratkan oleh pihak peluncur. Kata kunci: Satelit mikro, LAPAN-ORARI/A2, Pengujian struktur
Full Pages JTD Vol 18 No.2 Desember 2020 Editorial Jurnal Tekgan
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.a3522

Abstract

PENGARUH KETIDAKLURUSAN DAN KETIDAKSIMETRISAN PEMASANGAN SIRIP PADA PRESTASI TERBANG ROKET RX-250-LPN Sulistyo Atmadi
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.a778

Abstract

The performance of a rocket depend on several factor, one of which is the value of drag experienced during flight. This drag is contributed by the shape and the many components of the rocket. This paper discussed the fin misalignment and asymetrisness in respect to its main axis, which results in a change in the drag of RX-250-LPN rocket. The discussion was conducted with assuming the variation of this fin alignment from 1 degree to 2 degree. DATCOM was used to obtain aerodynamic parameters of the rocket. In addition, MATLAB 6.3 was used to calculate the performance of rocket. The knowledge of this fin misalignment can be used to get the minimum accuracy needed for better fin setting during rocket assembly.
PENINGKATAN REOLUSI PERHITUNGAN FREKUENSI GELOMBANG SINUS MENGGUNAKAN FFT (IMPROVING CALCULATION RESOLUTION OF SINE WAVE FREQUENCY USING FFT) Sri Kliwati
Jurnal Teknologi Dirgantara Vol.13 No. 1 Juni 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Perhitungan perubahan frekuensi sinyal sinus sangat penting untuk aplikasipada intrumentasi. Seperti pada sistem Doppler yang juga memerlukan perhitunganfrekuensi keluaran berupa gelombang sinus. Tulisan ini membahas peningkatanresolusi perhitungan perubahan frekuensi gelombang sinus berbasis algoritma FastFourier Transform (FFT). Penambahan waktu sampling data dapat meningkatkanresolusi frekuensi dengan signifikan, tetapi sampling data menjadi lebih rendah. Padaaplikasi frekuensi Doppler 440 MHz resolusi kecepatan sekitar 6.8 m/detik dengansampling data 10 Hz. Resolusi dan sampling data ini harus disesuaikan dengankecepatan dan durasi terbang roket agar optimal dalam pengukurannyaKata kunci: Resolusi frekuensi, gelombang sinus, FFT.

Page 29 of 34 | Total Record : 333

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