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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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Back Pages JTD Vol 16 No.1 Juni 2018 Redaksi Jurnal
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.a3018

Abstract

ON-BOARD FUNDAMENTAL FREQUENCY ESTIMATION OF ROCKET FLIGHT EXPERIMENTS USING DSP MICROCONTROLLER AND ACCELEROMETER Agus Harno Nurdin Syah; Sri Kliwati; Wahyu Widada
Jurnal Teknologi Dirgantara Vol 7, No.1 Juni (2009)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Fundamental frequency vibrasi roket pada saat terbang sangat penting diukur untuk pengembangan sistem elektronik maupun mekanik muatan roket. Tulisan ini membahas metode pengukuran fundamental frekuensi tersebut dengan menggunakan sensor accelerometer dan 32 bit DSP (Digital Signal Processor) microcontroller. CPU ini digunakan untuk akuisisi data dan perhitungan algoritma DFT (Discrete Fourier Transform) serta algoritma penentuan frekuensi fundamentalnya. Deteksi fundamental frekuensi berbasis envelope (lowpass filter) spektrum frekuensi. Sistem yang telah dibuat dapat dikombinasikan dengan radio modem untuk pengiriman data dengan kecepatan serta sampling rate yang cukup tinggi. Maksimum frekuensi yang dapat diestimasi hingga 2 kHz, cukup untuk parameter roket.
PENINJAUAN HOMOGENITAS PROPELAN SKALA K-ROUND BERDASARKAN VARIANS NILAI KALOR (HOMOGENEITY OBSERVATION OF PROPELLANT K-ROUND SCALE BASED ON CALORIFIC VALUE VARIANCE) Luthfia Hajar Abdillah Abdillah; Retno Ardianingsih
Jurnal Teknologi Dirgantara Vol. 12 No. 1 Juni 2014
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Impuls spesifik (Isp) propelan skala K-round yang dihasilkan Lapan masih tergolong rendah yaitu di bawah 220 detik. Selain itu dari dua propelan dengan komposisi sama sering diperoleh nilai Isp yang berbeda. Terjadinya perbedaan nilai Isp ini diperkirakan bahwa kedua propelan tersebut tidak homogen yang dapat menyebabkan kesalahan ukur dalam pengujian mekanik, balistik maupun pengujian statik sehingga data yang dihasilkan menjadi tidak valid. Oleh karena itu homogenitas propelan penting untuk diketahui. Homogenitas propelan diuji dengan cara perhitungan statistik melalui keseragaman varians data nilai kalor menggunakan metode uji F dan uji Bartlett. Berdasarkan hasil pengujian diperoleh bahwa nilai kalor sangat beragam dari 2015 kal/gram hingga 5829 kal/gram. Varians nilai kalor pada satu batang propelan dinyatakan tidak seragam yang berarti produk propelan skala K-Round yang dihasilkan tidak homogen. Adapun varians nilai kalor propelan pada batch yang sama dan pada batch yang berbeda dinyatakan seragam. Hal ini menunjukkan derajat perbedaan nilai kalor pada kedua macam batch tersebut konsisten yang berarti ketidak merataan distribusi bahan pada setiap batch produksi propelan K-Round juga konsisten.Kata kunci: Propelan K-round, Homogenitas, Nilai kalor, Uji F dan uji Bartlett, Varians
SIMULASI KINERJA SKEA DI KABUPATEN TIMOR TENGAH SELATAN MENGGUNAKAN WAsP Malik Ibrochim
Jurnal Teknologi Dirgantara Vol. 8 No.1 Juni 2010
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The analysis towards the performance of wind turbin simulation has been done in the District of Timor Tengah Selatan, Nusa Tenggara Timur Province by using the method of WAsP simulation. The data used as the simulation input are the wind speed and direction observed in Oelbukbuk vector map of TTS District and 3 (three) brands of 600kW wind turbin. The result shows that the performance of NEG-MICON wind turbine type NM 600-48 brand is better than 2 other brands (Vestas type V44 and Bonus type MKIV) that were simulated based on the wind climate and topography condition at TTS District NTT Province. Based on CF value, NEG-MICON type NM 600-48 wind turbine is 44,27 %, bigger than 2 other brands.
EVALUASI TEKNIK PENIMBANGAN HIDROSTATIK PADA PENGUKURAN DENSITAS PROPELAN PADAT KOMPOSIT Luthfia Hajar Abdillah; Afni Restasari; Kendra Hartaya; Ratna Rizky Puspitasari
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.a2868

Abstract

Densitas menjadi salah satu data karakteristik propelan padat komposit yang penting. Data nilai densitas propelan ini digunakan dalam proses simulasi dan perancangan motor roket untuk mendapatkan performa roket yang diinginkan. Pengukuran densitas yang dilakukan selama ini menggunakan teknik penimbangan hidrostatik yang melibatkan pengukuran berat sampel di dalam air, sehingga dimungkinkan terjadi penyimpangan hasil pengukuran. Untuk itu tujuan dari penelitian ini adalah untuk mengetahui besarnya penyimpangan nilai densitas propelan yang terjadi dan mengetahui cara pengukuran yang tepat melalui teknik penimbangan hidrostatik sehingga menghasilkan nilai densitas yang lebih sesuai. Beberapa sampel propelan diukur densitasnya menggunakan dua instrumen densitometer untuk melihat adanya penyimpangan hasil pengukuran. Dari hasil penelitian diperoleh bahwa penyimpangan nilai densitas propelan yang terjadi berkisar antara 2,08% hingga 5,58% dengan adanya “delay” pembacaan berat sampel di air.
SISTEM KONTROL SUN SEEKER SUATU MODEL UNTUK MENGENDALIKAN PERILAKU WAHANA ANTARIKSA Eko Budi Purwanto
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Sun seeker control system doing by monitoring the sun as main reference. The result of monitoring the sun position used for the line correction of space vehicle. In these paper used simulation method for gated parameter value control system. To know the influence of sun seeker control system, simulation was doing with and without lead compensator. The result of simulation show that without sun seeker control system the time settling is ts = 0.35 second and maximum overshoot Mp = 44,4 percent. These results not reasonable for controling of plan with high velocity like rocket and satellite. Later simulation with phase lead sun seeker control system, give settling time ts = 0,12 second and maximum overshoot Mp 5 percent. From the simulation data that sun seeker control system can used for space vehicle control and agree with steady state error specification.Keywords: Sun seeker control system, FFase lead, Waktu penetapan, lewatan maksimum, kondisi tunak
RANCANGAN DAN ANALISA ANTENA DI PERMUKAAN BADAN ROKET Sri Kliwati; Wahyu Widada
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.a791

Abstract

The antenna telemetry is usually placed in the body of LAPAN rocket for the launching campaign, which affected to the quality of radio communication. Especially, such effect increas the antenna overshadow to the surface of body rocket, which not influenced to the aerodynamic of rocket. This antenna was made by using the PCB plate with size of 1 cm width and 1 per 2 also 1 per 4 length for the frequency of 900 MHz
ANALISIS DATA SENSOR ACCELEROMETER PADA UJI TERBANG ROKET EKSPERIMEN LAPAN TIPE RX–200 (ANALYSIS SENSOR DATA ACCELEROMETER IN FLIGHT TEST ROCKET EXPERIMENT LAPAN TYPE RX-200) - Kurdianto; Endro Artono
Jurnal Teknologi Dirgantara Vol. 13 No. 2 Desember 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Roket RX–200 adalah jenis roket model balistik dengan diameter 200mm. Roket ini dilengkapi dengan muatan (payload) berupa sensor pengindera gerak berbasiskan mikroprosesor berupa 6-Degree of Freedom (6-DOF) Inertial Measurement Unit (IMU) dan sistem telemetri onboard dengan menggunakan frekuensi 900MHz. Karakteristik terbang roket RX-200 saat uji terbang dapat dianalisis dari data sensor pengindera gerak yang diterima menggunakan antena omni 900MHz dan antena yagi 900MHz. Dari data yang diterima, roket mengalami percepatan hingga sebesar 19.2G, burning out terjadi pada detik ke 7.09, dengan ketinggian terbang roket dari General Position System (GPS) mencapai 1952 m atau 1.9 Km.Kata Kunci: Sensor Accelerometer, Mikroprosesor, Ground station
PEMODELAN SISTEM DAN ANALISIS KESTABILAN DINAMIK PESAWAT UAV (MODELING SYSTEM AND DYNAMIC STABILITY ANALYSIS OF UAV) Eko Budi Purwanto
Jurnal Teknologi Dirgantara Vol 10 No.1 Juni 2012
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Mission of Unmanned Aerial Vehicle (UAV) “Elang Avionik” is surveillance and aerial photographs. Therefore the flight of UAV must be stable and controlable, and first step activity is dynamic modelling and stability analisys. The problems of UAV system is disturbance, noise of sensor, MIMO and uncertainty dynamic model. For good result using the multivariable robust control, with some step research that is: (1)modeling and stability analysis, (2) design and implementation of PID control system, (3) flight dynamic parameter identification, (4) design and implementation of hardware in the loop simulation, (5) design and implementation of multivariable robust control, (6) test and evaluation of system. Simulation result show that the eigen value in longitudinal is: phugoid mode = –0,061293±0,40526i and non-oscillation mode = –6,1121±4,9253. In lateral directional is:dutch roll mode = –0,91089±5,7994i, spiral mode= –0,036563, and roll subsidence mode = –12,7181. Location of poles system on the left of imaginary axis, the means that the character of system is dynamic stable. But settling time to steady state condition is very long and improved by control system design. Key word: State space, Longitudinal, Lateral, Stable static, Stable dynamic
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

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