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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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METODE DOPPLER RADIO UNTUK MENGUKUR KECEPATAN ROKET RX200 [RADIO DOPPLER METHOD FOR MEASURING VELOCITY OF ROCKET RX200] Wahyu Widada
Jurnal Teknologi Dirgantara Vol.10 No.2 Desember 2012
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

This paper discusses the methods and design of radio Doppler to measure the speed of the rocket type RX200. Doppler system consists of a radio transponder to emit a continuous radio signal from the rocket and the radio base station to measure the change in frequency of the radio signal. A change in the frequency of the radio signal caused by the speed of the rocket is used to measure the speed and position of the rocket. The design of radio frequency is 880 MHz transponder adapted to the design speed of the rocket RX200. This method is relatively easy to implement compared with the radar transponder system that has been developed. A simulation of Doppler frequency is performed using the radar data transponder rocket launch experiment RX200 and recomendation of bandwith radio receiver should be 4000 Hz. The combination of these two systems will make a more acurate and reliable tracking system. Key words: Doppler tracking, Radio transponder, Frequency variation
CHARACTERIZATION OF SIZE AND SHAPE OF AMMONIUM PERCHLORATE PARTICLE FROM CHINA, SOUTH KOREA, AND INDONESIA AND THEIR INFLUENCES ON PROPERTIES OF PROPELLANT Jones Hutauruk
Jurnal Teknologi Dirgantara Vol. 18 No.1 Juni 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.a3346

Abstract

The aim of this study is to obtain characteristics of ammonium perchlorate particle that used in Rocket Technology Center (LAPAN). Characterization begin from the determination of particle size distribution with Particle Size Analyzer. The SEM is used to obtain information about the morphology of AP, furthermore, the results are reprocessed using ImageJ software to analyze the shape of AP particle, and the Surface area was obtained by using BET. Characteristic of AP such as particle size, shape, and surface area are important parameters because those are directly related to propellant combustion energy. Ammonium perchlorate was procured from China, South Korea, and Indonesia with a particle size of 200µm From this study, the particle size of APC200, APH200 and API200 was obtained, which are 265 µm, 236 µm, and 242 µm, with particle shape aggregate value of 0,68, 0,38 and 0,33, roundness of 0,57, 0,79,0,63, and surface area of 1,104 m2/g, 5,561 m2/g, and 2,972 m2/g.
PENELITIAN PRESTASI TERBANG ROKET SONDA SATU TINGKAT RX-320 Turah Sembiring
Jurnal Teknologi Dirgantara Vol 6, No.2 Desember (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Penelitian prestasi terbang roket telah dilakukan terhadap roket RX-320 dengan sudut elevasi bervariasi dari 50º sampai dengan 80º. Bahan pendorong yang dipakai adalah jenis propelan HTPB. Uji statik roket berbobot 598 kg, berat propelan 254 kg menghasilkan gaya dorong 3500 kgf dan waktu pembakaran 13 detik. Dengan uji penerbangan telah dihitung presentasi terbang roket maksimum untuk berbagai sudut elevasi. Jarak jangkauan maksimum yang dicapai adalah 45,223 km dengan sudut elevasi 65º, tinggi maksimum yang dicapai adalah 27,595 km dengan sudut elevasi 80º, kecepatan maksimum yang dicapai adalah 2,531 mach dengan sudut elevasi 50º dan waktu terbang maksimum yang dicapai adalah 160 detik dengan sudut elevasi 80º.
PENENTUAN KANDUNGAN OKSIDATOR BERDASAR REAKSI STOIKIOMETRI DAN STRUKTUR KRISTAL DALAM RANGKA ADOPSI FORMULASI PROPELAN HLP (DETERMINATION OF OXIDATOR CONTENT BASED ON STOICHIOMETRICAL AND CHRYSTAL STRUCTURE ON PURPOSE OF HLP PROPELLANT FORMULATION ADOPTION) Kendra Hartaya; Luthfia Hajar Abdillah; Retno Ardianingsih
Jurnal Teknologi Dirgantara Vol. 12 No. 2 Desember 2014
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Telah dilakukan penentuan komposisi propelan LAPAN berdasar formulasi propelan HLP. Penentuan komposisi propelan LAPAN berdasar pada stoikiometri reaksi pembakaran HTPB dan pembakaran Al oleh AP. Berdasarkan stoikiometri ini diperoleh prosentase AP adalah 68% sehingga HTPB 31% dan Al 1%. Selanjutnya rasio AP kasar (200μm) terhadap AP Halus (70μm) ditentukan berdasar asumsi bahwa struktur yang terbentuk oleh sekumpulan butiran AP adalah Body Center Cubic (BCC). Berdasar asumsi BCC, jika radius AP kasar R, maka radius AP halus r=41,42%, atau jika AP kasar 200μ maka AP halus 83μm. Dalam satu satuan sel BCC, terdapat 2 butir AP kasar dan 3 butir AP halus sehingga rasio AP kasar-AP halus = 2/3 AP kasar yang sesuai dengan propelan HLP adalah ukuran 180-280μ (rata-rata ukuran r=165 μ, ruang kosong r=29.10-4μ). Karena tidak ditemukan supplier AP ukuran kurang dari 100μ, diduga AP halus propelan HLP adalah rekayasa dari AP ukuran besar, atau diperoleh melalui kerjsasama khusus. Komposisi propelan Lapan berdasar formulasi HLP, mengandung AP 68% (campuran AP Kasar dan AP halus), AP kasar 200μ (R) AP halus 83μ (r=41,42%) atau AP kasar 165μ, AP halus 29.10-4μ.Kata Kunci : Oksidator, Propelan, HLP
ANALISIS DAN OPTIMASI SUDU SKEA 5 KW UNTUK PEMOMPAAN Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 8, No.2 Desember (2010)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

LAPAN Wind Energy Conversion System (WECS) for pumping (SKEA-MARUTO) has a rotor diameter of 4.5 m and 6 number of blades. The blade used is a curved plate area. The result of recalculation has shown that operational condition on 10 m/sec wind speed and 100 rpm rotational speed, the rotor produces 4.74 kW. By assuming of 20% generator losses, the SKEA will produces power of 3.79 kW. To improve this performance to 5 kW, the rotor diameter has to be increased to 6 m. Chord and twist distribution are made similar to the previous design, and remain unchanged. Calculation is made by varying number of blades and blade rotation. At the wind speed of 10 m/sec and the rotational speed of 100 rpm, the SKEA able to produce the power of 6.36 kW. Key words:WECS, 5 kW, curved plate
CHARACTERISTIC OF MUS-01 WING’S STRUCTURE TESTING MODEL Aryandi Marta; Atik Bintoro; Riki Ardiansyah
Jurnal Teknologi Dirgantara Vol. 16 No. 2 Desember 2018
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a2962

Abstract

The characteristic model of MUS-01 wing structure testing has been performed. Planned, this model will be used as an unmanned wing of the LSU-03NG. The test model is made of composite type e-glass. At the time of testing the structure test model is loaded according to MTOW weight. This research method also involves the unmanned aircraft mission, especially on the model test structure, model dimension, and direct experiment in the form of loading on the test model. The result of characterization of the test model during test, showed that the indicated test model has the characteristics as a test model that is unable to accept the unmanned operational load of LSU-03NG series aircraft. So it can not be used as a consideration for the structure of the unmanned aircraft.
ANALISA PENGARUH SUDUT PITCH, UNTUK MEMPEROLEH DAYA OPTIMAL TURBIN ANGIN LPN-SKEA 50 KW PADA BEBERAPA KONDISI KECEPATAN ANGIN Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 7, No.1 Juni (2009)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Kurva daya merupakan indikator utama prestasi sebuah turbin angin. Dengan sudut pitch tertentu, turbin angin mempunyai kurva daya yang tertentu juga. Rotor dirancang agar turbin angin LPN-SKEA 50kW dapat menghasilkan daya 50 kW pada kecepatan angin 10 m/det dan kecepatan putar 80 rpm. Penambahan sudut pitch biasanya dilakukan untuk menambah torsi awal rotor sehingga rotor menjadi lebih mudah berputar dari kondisi diam. Pengaruh penambahan sudut pitch adalah berkurangnya kecepatan putar rotor sehingga daya yang dihasilkan juga menjadi lebih kecil. Hasil perhitungan menunjukkan bahwa penambahan sudut pitch hingga 10º akan mengurangi daya dari 50 kW menjadi 23,3 kW pada kecepatan angin 10 m/det. Dengan penambahan sudut pitch yang sama dan dengan mengasumsikan bahwa kurva daya merupakan polinomial pangkat tiga, maka daya sebesar 50 kW dapat dicapai pada kecepatan angin 12,9 m/det.
OPTIMASI SISTEM LINING MOTOR ROKET PADAT RX1220 MELALUI PERUBAHAN KOMPOSISI MATERIAL LINER DAN METODE LINING (OPTIMIZATION OF LINING SYSTEM FOR RX1220 SOLID ROCKET MOTOR THROUGH IMPROVEMENT OF LINER MATERIAL COMPOSITION AND LINING METHOD) Wiwiek Utami Dewi
Jurnal Teknologi Dirgantara Vol. 12 No. 1 Juni 2014
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Pada tahun 2013, sebanyak 21,42% motor roket RX1220 yang diproduksi dinyatakan tidak lulus uji radiografi karena memiliki banyak rongga udara pada lapisan liner-nya (cacat liner). Tahun 2014, terjadi perubahan dimensi diameter dalam tabung motor roket dari 107,5 mm menjadi 107,1 mm. Perubahan dimensi ini membuat celah liner semakin sempit (1,5 mm menjadi 1,3 mm). Proses pengecoran dengan metode gravity casting menjadi semakin sulit. Viskositas liner yang tinggi akan menjadi hambatan utama keberhasilan proses liner. Upaya penurunan viskositas sudah dilakukan namun belum memberikan hasil terbaik. Perubahan komposisi liner dan metode lining-nya telah dilakukan untuk mengoptimasi proses lining roket RX1220. Optimasi memberikan hasil yang diharapkan. Setelah liner komposisi baru dan perbaikan metode lining diterapkan, tidak ada lagi motor roket RX1220 yang dinyatakan tidak lulus uji radiografi (cacat liner).Kata kunci : Material liner, Metode lining, Motor roket padat, RX1220
ALGORITMA PENGENALAN POLA BINTANG UNTUK DETEKSI POSISI BINTANG PADA STAR SENSOR SATELIT LAPAN M. Arif Saifudin; Robertus Heru Triharjanto
Jurnal Teknologi Dirgantara Vol. 8 No.1 Juni 2010
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Star sensor is a high accuracy sensor for a satellite attitude determination. This sensor identifies the position of stars in celestial map by comparing the position of stars on its active sensor with the star position data contained in its catalogue. An algorithm is needed to recognize the star pattern imaged by sensoring and calculating the position of the stars. An efficient and accurate algorithm is needed to improve the performance of the star sensor for satellite attitude determination. A simple star pattern recognition algorithm uses the neighbourhood technique. The first approach of algorithm is detecting the brightest star and its neigbours in the sensor Field of View (FOV) and identifying whether the stars in image sensor are fit to the star pattern in the catalogue. The simple catalogue used contains the star position and all its neighbouring stars within particular distance in the scope of FOV. Test result showed that neighbours technique has an accuracy below 1 arc min which correspond to the typical accuracy value of star sensor.
Time Optimization for Lossy Decompression of the LISA Sensor Data on LAPAN A3 Satellite Using a Grouping Method of HUFFMAN Code Bit Number Suhermanto M.T
Jurnal Teknologi Dirgantara Vol. 16 No. 1 Juni 2018
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2018.v16.a2960

Abstract

The LAPAN-A3 satellite provides compressed multispectral data from LISA sensor using real-time lossy compression. The compression of the multispectral data of radiometric resolution 12bit/pixel is built from the Fourier transform and the use of Huffman decoder 514 binary length code. A problem arised in the data extraction process, that decompression performance is very slow because the search method of code value in Hufman table was done sequentially from one bit to the next bit in one block of data along 4000 pixels. The data extraction time for one scene in 12 minutes acquisition duration (one full path) takes up to 20 hours. This paper proposes a method of improving the LISA real-time lossy data decompression algorithm using the grouping method of bit code on the Huffman decoding algorithm and using pointer for reading data in the buffer memory. Using this method, the searching process of bit code for all characters in the Huffman decoder algorithm is done regularly, so the search processing time is significantly reduced. The performance test used 6 data samples. The result showed that extraction time has an average of 14 times faster. The lossy compression ratio is still in accordance with the design specification of LISA sensor that is less than 4 times and the appearance of the special character is very small i.e. less than 0.5%.

Page 5 of 34 | Total Record : 333

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