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Heri Budi Wibowo
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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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ANALISIS MODUS NORMAL DAN KEKUATAN STRUKTUR SIRIP ROKET-168 DARI BAHAN AL-PLATE - Sugiarmadji; - Setiadi
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.a793

Abstract

Structural strength analysis on Motor Rocket-168 fins was carried out to determine static stresses due to aerodynamic loadings. Here, 90 mm of the root chord area from leading edge was unclamp (free). The analysis results showed the maximum value of von Mises stress is Q von mises = 42.40 MPa. For 90 mm condition un clamp (free) we obtained the safety factor of the material for fins structures made of Al-Plate is SF=3.39. For 67.5 mm of 90 mm root chord area constrainted at 12456 directions, it was found Qvm equal 11,26 MPa and has higher safety factor. Eigenvalues and eigenvectors of the fins structures. The results showed that the eigenvalues of the fin structures are Q1 equal 198,47 Hz, Q2 equal 616,34 Hz, Q3 equal 1080,97 Hz, Q4 equal 1704,33 Hz, Q5 equal 2386,82 Hz, dan Q6 equal 2770,94 Hz.
IMPLEMENTASI CHIRP SIGNAL GENERATOR PADA FPGA UNTUK MISI PENCITRAAN LAPAN SURVEILLANCE AIRCRAFT - SYNTHETIC APERTURE RADAR (LSA-SAR) (IMPLEMENTATION OF CHIRP SIGNAL GENERATOR ON FPGA FOR IMAGING MISSION OF LAPAN SURVEILLANCE AIRCRAFT - SYNTHETIC APERTURE Andi Mukhtar Tahir; Ade Putri Septi Jayani
Jurnal Teknologi Dirgantara Vol. 13 No. 2 Desember 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Radar bekerja dengan memanfaatkan sinyal gelombang elektromagnet yang dihasilkan olehperangkat waveform generator. Sinyal yang dipancarkan oleh radar akan dipantulkan sebagian olehtarget dan pantulan ini ditangkap oleh radar untuk diolah dengan cara membandingkan sinyal yangdipancarkan dengan sinyal yang dipantulkan kembali sehingga menghasilkan informasi berupakecepatan, jarak, atau citra dari suatu target. Waveform generator merupakan perangkat yang memegangperanan awal dalam sebuah sistem radar yang turut menentukan kinerja dari suatu sistem radar,oleh karena itu pada penelitian ini penulis akan membuat sebuah waveform generator sebagailangkah awal dalam percobaan di bidang teknologi radar. Waveform generator yang dibuatmenghasilkan sinyal chirp dengan menggunakan metode Direct Digital Synthesizer (DDS) yangmenggunakan memori yang lebih kecil dibandingkan Memory-based Chirp Generator, karena sinyalreferensi yang digunakan hanya berupa sebuah sinyal sinus dan cosinus. DDS chirp generator inidiimplementasikan pada board Field Programmable Gate Array Altera tipe Cyclone IV yang merupakandevelopment board produksi Terasic tipe DE2-115 dan menghasilkan keluaran berupa sinyal chirp.Hasil pengukuran sinyal keluaran menggunakan osiloskop menunjukkan sinyal chirp denganfrekuensi sampling 200 MHz, jumlah sample 6415 dan periode sampling 32 us, sedangkanpengukuran menggunakan spectrum analyzer terlihat terjadi pergeseran nilai frekuensi sehinggabandwidth tercapai sebesar 75,9 MHz. Namun secara keseluruhan hasil ini menunjukkan bahwasistem berjalan dengan baik.Kata kunci: Radar, Chirp generator, DDS chirp generator
PENGEMBANGAN PERANGKAT LUNAK ANALISIS LINTAS TERBANG ROKET MULTI-STAGE (DEVELOPMENT OF TRAJECTORY ANALYSIS SOFTWARE FOR MULTI-STAGE ROCKET) Ridanto Eko Poetro; Yazdi I. Jenie; Rianto Adhy Sasongko; Satriya Utama
Jurnal Teknologi Dirgantara Vol 10 No.1 Juni 2012
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

This paper discusses the development of a computer software for simulating and analyzing flight trajectory of rocket systems. Many aspects may influence the trajectory, such as those related to the internal characteristic of the system, those representing external or environmental influence, and also the ones corresponding to the procedures of the launching and the operation during its flight. The software is developed based on the mathematical equations representing the balance of forces and moments occur during the flight of a rocket. Some conditions related to rocket internal characteristic variation, external perturbance, and flight procedure/operation are represented as parameters variations of the mathematical equations used for computing the rocket system attitude and movement variables. The software, developed using MATLAB/ SIMULINK application, is then used for simulating and analyzing the flight trajectory of a multi-stage rocket in some flight conditions. At this development stage, as the simulation results show, the software can perform its function quite well to compute the system variables during each of its flight phases and display the information required for further analysis. In future development, some validation tests still need to be accomplished for ensuring the accuracy and validity of the method used in this software. Keywords: Rocket, Flight Trajectory, Simulation
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.
SISTEM KENDALI ROKET UNTUK GERAK UNPITCHING Rika Andiarti; Edi Sofyan
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

A missile control system utilizing Proportional-Integral-Derivative (PID) controller is proposed. With this controller, the missile is constrained to flight with zero pitch angle. By choosing LAPAN's missile RKX-100 as a dynamic model, this PID controller is applied. Simulation results show that the applying controller seems to be effective in missile unpitching manuver. Keywords : PID Controller, Missile, Unpitching
KENDALI SAKELAR EMPAT ANTENNA BERSUSUN UNTUK PENJEJAKAN INTERFERENCE FREKUENSI TTC SATELIT LAPAN (SWITCH CONTROL SYSTEM FOR FOUR ARRAY ANTENNA FOR TRACKING OF LAPAN’S SATELLITE TTC INTERFERENCE FREQUENCY) Arif Hidayat; Wahyudi Hasbi; Elyas Palantei; Syafruddin Syarif
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.a2631

Abstract

Telemetry Tracking and Command (TTC) of LAPAN’s satellite use UHF frequency. This frequency is susceptible to interference by an amateur radio transmitter. One method to look for an interference transmitter is Doppler Effect. To get the optimal value of the Doppler shift frequency, it is necessary to have stabilized antenna switch as controller of antenna array. The RF switches controlled by an Arduino board produced 500 Hz Doppler frequency. Other hardwares are Demodulator, clock Arduino Board, and Universal Serial Bus  (USB) soundcard as the input for the searching software. The results can be shown using the open access sound Doppler. The system has been able to detect UHF transmitters and repeaters received by the device. For upgrade, the data processing system can be done using Matlab software to easier process and analysis. AbstrakTelemetry Tracking And Command (TTC) satelit LAPAN menggunakan frekuensi UHF. Frekuensi UHF rentan terhadap interference. Salah satu metode mencari pemancar interference menggunakan metode efek Doppler. Untuk mendapat nilai pergeseran frekuensi sesuai efek Doppler yang dibutuhkan, diperlukan sakelar antena yang stabil, yang berfungsi sebagai pengontrol antena array. Rangkaian sakelar RF di kontrol dengan Arduino board menghasilkan Doppler frekuensi 500 Hz. Demodulator, clock Arduino Board dan Soundcard sebagai input software pencari.  Hasil outputnya dapat dilihat dengan menggunakan software open akses sounDoppler. Sistem ini mampu mendeteksi pemancar maupun repeater yang diterima oleh perangkat. Upgrade sistem dari penelitian ini adalah proses pengolahan data dapat dilakukan secara mandiri menggunakan software Matlab sehingga lebih mudah untuk diolah dan dianalisis.
RANCANG BANGUN DATA AKUISISI MULTI KANAL UNTUK DOPPLER TRACKING SISTEM PELUNCUR ROKET JAMAK (DESIGN AND DEVELOPMENT OF MULTI CHANNEL DATA ACQUISITION FOR DOPPLER TRACKING OF MULTIPLE LAUNCH ROCKET SYSTEM) Wahyu Widada
Jurnal Teknologi Dirgantara Vol. 11 No.2 Desember 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Makalah ini membahas hasil desain dan pengembangan Sistem Data Akuisisi biaya rendah dengan Universial Serial Bus (USB) untuk pengukuran sinyal Doppler tracking roket. Sinyal Doppler mempunyai rentang frekuensi antara 0 hingga 3000 Hz bergantung pada perubahan kecepatan roket dan frekuensi radio. DAS ini dirancang menggunakan mikrokontroler ATMega32, 8 kanal simultan dengan 16 bit Analog Digital Converter (ADC), komunikasi dengan Personal Computer (PC) melalui USB. DAS ini telah diuji dengan program aplikasi yang dikembangkan di MATLAB, yang dapat memantau secara realtime 8 kanal sinyal Doppler dalam grafis serta tampilan numerik dengan sampling 16 KHz. DAS ini akan digunakan untuk aplikasi pada peluncuran roket Multiple Launch Rocket System (MLRS). Kata kunci: Data akuisisi multi-kanal, Doppler receiver, Tracking roket, MLRS
PERHITUNGAN BEBAN KRITIS STRUKTUR PLASTIS DENGAN MENGGUNAKAN METODE SOUTHWELL Darwin Sebayang
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.a779

Abstract

The structure of the cylinder can be found in the structure of a rocket, an aircraft of chimney. The stability of the cylinder is very important to know the capability cylinder to support the load. It is required to give a load up to plastic region in order to optimize the load capability of the material. Therefore it is required to obtain the procedure to calculate the plastic buckling. Herewith it is shown the Southwell's Method to calculate the plastic buckling of the cylinder made of the non linear material. The approximation based on the Ramberg-Osgood is used to illustrate the stress-strain diagram. The diagram of Karman is used to obtain the Modulus of elasticity which is valid for the plastic region. The result based on this method are campared to the experimental data. The results are satisfactory. This method can be used to calculate the critical load of the LAPAN's rocket by considering the plasticity of the material and structure can be lighter.
METODE DOUBLE EXPONENTIAL SMOOTHING UNTUK ESTIMASI POSISI ROKET MENGGUNAKAN RADAR TRANSPONDER (DOUBLE EXPONENTIAL SMOOTHING METHODS FOR ESTIMATING POSITION ROCKET USING RADAR TRANSPONDER) Wahyu Widada
Jurnal Teknologi Dirgantara Vol. 13 No. 2 Desember 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Data posisi sistem radar transponder masih mengandung derau signal, oleh karena itu perlu memproses algoritma estimasi dan digunakan untuk mengetahui posisi waktu berikutnya. Tulisan ini membahas estimasi posisi roket dari hasil pengukuran radar transponder dengan menggunakan metode double exponential smoothing. Metode ini diimplementasikan pada hasil pengukuran radar transponder uji terbang roket RX122. Hasil eksperimen menunjukkan bahwa posisi roket dapat diestimasi menjadi lebih akurat dengan analisa nilai Root Mean Square Error (RMSE) sebesar 0,67 dan nilai tersebut sekitar 2,2 kali lebih kecil.
PEMBUATAN DAN ANALISIS KINERJA SISTEM THERMAL INSULATION PADA MOTOR ROKET YANG MENGGUNAKAN PROPELAN CASE-BONDED - Sutrisno
Jurnal Teknologi Dirgantara Vol 9, No. 2 Desember (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 Liner material of case-bonded propellant rocket motor have been made by adding some filler to the liner material composition used in free standing rocket motor. The liner was manufactured by spinning method to the rocket motor tube. The case-bonded liner performance in radial burning rocket motor was analyzed using material characteristic test result combined with rocket motor burning mechanism and free standing rocket motor static test result. The case-bonded liner materials are superior to the free standing liner because it is lighter (18,94%) and have higher heat resistance (6,75%). The application of case-bonded liner for radial burning rocket motor using single configuration propellant will be safe because the heat of propellant combustion passed through the isolator materials before the rocket motor tube. Based on the analysis it is found that the case-bonded liner can be recommended to the radial burning rocket motor using single configuration propellant. Keywords: Liner, Free standing, Case-bonded

Page 6 of 34 | Total Record : 333

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