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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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RANCANG BANGUN PROTOTIPE SISTEM HEADING AUTOPILOT BERBASIS RATE-GYROSCOPE DAN MICROCONTROLLER Wahyu Widada
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

This paper discusses an experiment result of the prototype system feedback control for vehicle heading autopilot. The heading angle is measured with a rate-gyroscope and controlling with a control system based on a microcontroller and a stepper motor. This system is successfully realized within 0.5 degree of the error for heading angle. The accuracy of heading sensor is decrease due to vibration from stepper motor. To overcome such problem we recommended to use an analog lowpass filter and a mounting anti vibration. Keywords: Heading autopilot, Rate-gyroscope, Stepper motor, AVR microcontroller.
DESAIN DAN IMPLEMENTASI GROUND MODEL SATELIT NANO DENGAN SUBSISTEM KOMUNIKASI PADA FREKUENSI S-BAND (DESIGN AND IMPLEMENTATION OF GROUND MODEL NANO-SATELLITE WITH S-BAND FREQUENCY COMMUNICATION SUBSYSTEM) Fitrenna Khaznasari; Joko Suryana
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.a2372

Abstract

This paper discusses about the design of the Earth observation ground model nano-satellite which communication subsystem works in S-BAND frequency. This ground model nano-satellite refers to GOLIAT satellite which has the size of 10 x 10 x 10 cm, weighs one kilogram, brings camera as its payload, and has a power emittion of 1 watt. The ground model has a microstrip antenna with the size of 9,5 x 9,5 cm, works in frequency of 2,4 GHz, has the parameter of S11 -18,506 dB, the VSWR equals to 1,2695, and has gain of 6,42 dB. The ground model was made from Seeduino as an on-board computer, XBee module for communication, VC0706 camera, lithium ion battery, solar cell, and various sensors. The calculation of link budget at 300km distance for the ground model is Effective Isotropic Radiated Power (EIRP) equal to 36,42 dBm, receive power equals to -101,18 dBm, receive power and noise ratio ( equal to 107 dBHz, and energy bit and noise ratio equal to 55,02 dB, while GOLIAT satellite has EIRP of 32,2 dBm, receive power of -82 dBm, receive power and noise ratio of 126,18 dBHz, and energy bit and noise ratio equal to 86,357 dB. Therefore, it could be concluded that the design and implementation of nano-satellite with S-band communication system has been successfully done, moreover, the performance is better than the satellite design used for comparison.  Abstrak:Makalah ini berisi desain dari ground model nano-satelit pengamat Bumi yang subsistem komunikasinya bekerja pada frekuensi S-Band. Ground model yang dibuat mengacu pada satelit GOLIAT yang memiliki ukuran sebesar 10 x 10 x 10 cm, berat satu kilogram, payload yang dibawa berupa kamera, dan daya yang dipancarkan sebesar 1 watt. Ground model satelit nano yang dibuat memiliki antena untuk transmisi berupa antena mikrostrip dengan ukuran 9,5 x 9,5 cm, frekuensi kerja 2,4 GHz, nilai parameter S11 sebesar -18,506 dB, VSWR sebesar 1,2695, dan gain sebesar 6,42 dB. Ground model yang dibuat menggunakan Seeeduino sebagai on-board computer, modul XBee untuk berkomunikasi, kamera VC0706, baterai lithium ion, solar panel, dan berbagai macam sensor. Perhitungan link budget pada jarak 300 km untuk ground model satelit nano yang dibuat yaitu Effective Isotropic Radiated Power (EIRP) yang dimilikinya sebesar 36,42 dBm, daya terima -101,18 dBm, receive power dan noise ratio (  sebesar 107 dBHz, dan energy bit dan noise ratio sebesar 55,02 dB, sementara untuk satelit GOLIAT memiliki EIRP sebesar 32,2 dBm, daya terimanya sebesar -82 dBm, receive power dan noise ratio sebesar 126,18 dBHz, dan energy bit dan noise ratio sebesar 86,357 dB. Sehingga dapat disimpulkan bahwa desain dan implementasi ground model satelit nano dengan subsistem komunikasi S-band berhasil dilakukan, bahkan kinerjanya lebih baik dari satelit pembanding.
DESAIN DAN IMPLEMENTASI FLIGHT CONTROLLER DENGAN IMU 6-DOF DAN METODE QUATERNION UNTUK APLIKASI AERO ROBOT (DESIGN AND IMPLEMENTATION OF FLIGHT CONTROLLER USING IMU 6-DOF AND QUATERNION METHOD FOR AERO ROBOT APPLICATION) Nurmajid Setyasaputra
Jurnal Teknologi Dirgantara Vol. 11 No.2 Desember 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Aero Robot atau Unmanned Aerial Vehicle (UAV) semakin populer di kalangan peneliti seluruh dunia atas fleksibilitas dan kemampuan untuk melakukan sebuah misi, seperti melakukan pengawasan di daerah perbatasan, mengambil foto udara di daerah terpencil, identifikasi kerusakan daerah bencana, dan lain-lain. Keuntungan dari UAV utamanya adalah dapat menjangkau daerah yang sulit dan berbahaya tanpa membahayakan nyawa pilot. Pada UAV seperti jenis quadrotor dibutuhkan sebuah perangkat elektronik yang mengukur dan melaporkan kecepatan, orientasi, dan gaya gravitasi dengan kombinasi akselerometer dan giroskop yaitu Inertial Measurement Unit (IMU) yang minimal memiliki 6 DOF (Degree of Freedom) yaitu 3-axis akselerometer dan 3-axis giroskop. Oleh karena itu, dibutuhkan sebuah perangkat yang dapat digunakan untuk mengukur, melaporkan, dan melakukan umpan balik agar dapat melakukan penyeimbangan pada quadrotor. Solusinya adalah dengan mendesain dan implementasi sebuah flight controller. Pada kesempatan ini dilakukan penelitian dengan mengkombinasikan akselerometer dan giroskop untuk menyeimbangkan sikap quadrotor dengan menggunakan Quaternion untuk konsistensi kestabilan quadrotor pada parameter kemiringan sudut sikap pitch dan roll. Hasil penelitian telah menunjukkan sensor dan quaternion telah bekerja dengan baik dan sesuai. Kata kunci: IMU, Quadrotor, Flight Controller, Quaternion
Front 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.a3521

Abstract

RANCANGAN KAPAL UDARA (AIRSHIP) UNTUK VIDEO MONITORING DARI UDARA - Sugiarmadji HPS; Robertus Heru T; - Setiadi; - Ediwan
Jurnal Teknologi Dirgantara Vol 1, No.1 Juni(2003)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Remotely controlled non rigid helium airship type is chosen in airship design criteria for video monitoring. The design consists of airship dimensions and volume determination, maximum take of weight (MTOW) and W (weight empty plus payload) calculations, weight and structures analysis, airship stabilization analysis, airship guidance system, power plant system, position monitoring system, material and process, and payload systems. Here, Helium gas will be filled for generating a lift that is equal to the weight of the displaced air. An Airship Demonstrator Model LPN-01 is built to represent the design results. The model has length of L=8.5 m and 2.2 m diameter, so that the envelope volume is of 20 m. This Demonstrator Model will be used for studying capability or performance of airship, especially on ascent and descent manuever, airship's stability, position monitoring and payloads.
MODEL DISTORSI PEMBIASAN ATMOSFER PADA CITRA SATELIT LAPAN-A2 DAN LAPAN-A3 (ATMOSPHERIC REFRACTION DISTORTION MODEL ON LAPAN-A2 AND LAPAN-A3 SATELLITE IMAGE) Patria Rachman Hakim
Jurnal Teknologi Dirgantara Vol.13 No. 1 Juni 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Citra satelit umumnya memiliki distorsi baik dalam hal geometri maupun radiometri. Salah satu distorsi geometri yang umum terjadi pada citra satelit adalah distorsi yang diakibatkan karena terjadinya proses pembiasan cahaya oleh atmosfer. Dengan adanya pembiasan atmosfer, perhitungan proyeksi obyek di permukaan bumi pada bidang kamera menjadi rumit dan memerlukan proses komputasi yang cukup panjang. Makalah ini memodelkan distorsi pembiasan atmosfer tersebut dalam persamaan sederhana berdasarkan variabel orientasi kamera dan ketinggian satelit. Metode regresi linear least square digunakan untuk mengidentifikasi model persamaan dengan tingkat kesalahan terkecil. Hasil identifikasi menunjukkan bahwa distorsi pembiasan atmosfer pada citra satelit LAPAN-A2 dan LAPAN-A3 dapat dimodelkan menggunakan persamaan rasional orde-3 dengan hanya satu peubah yaitu orientasi kamera atau persamaan rasional orde-1 dengan dua peubah yaitu orientasi kamera dan ketinggian satelit. Hasil simulasi modul koreksi citra menunjukkan bahwa dengan menggunakan model persamaan yang diajukan maka perhitungan distorsi geometri pada citra satelit dapat dilakukan dengan lebih cepat tanpa mengurangi akurasi geometri citra secara signifikan.Kata kunci: Citra satelit, Distorsi geometri, Pembiasan atmosfer, Least-square
UPAYA PENINGKATAN KUALITAS GEOMETRIK CITRAUPAYA PENINGKATAN KUALITAS GEOMETRIK CITRA LAPAN-TUBSAT PADA APLIKASI SURVEILEN Catur Aries Rokhmana; Chusnul Tri Judianto
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 Indonesia has developed and operates the LAPAN-TUBSAT micro satellite since 2007 for supporting the surveillance application to observe the earth surface. LAPAN-TUBSAT satellite carried a video camera as an imaging sensor with 5 m ground resolution and 3.5 km swath. Data from this camera still have a weak geometric. This paper will reviews regarding LAPAN-TUBSAT data processing from video recordings as an effort to increase the geometric quality of the LAPAN-TUBSAT image. The correction model rectification of a simple single photograph is used for geometric correction. While the using of super resolution operator for increasing the video image resolution. The correction model rectification of a simple single photograph is used for geometric correction. While the super resolution operator attempted to efforts to increase the resolution of the video image. The experimental results shows geo-reference image with better geometric quality. The evaluation of LAPAN-TUBSAT performance should be carried out In the near future especially for providing Altitude information (Z). This is related to satellite manoeuvre ability to generate a stereo image with better B/H ratioKeywords:Videography system, LAPAN-TUBSAT Satellite, Geometric image improvement
EFFECT OF FLAT AND HEMISPHERICALLY ENDED CYLINDER BIRD MODEL WITH FINITE ELEMENT MODELLING OF BIRD STRIKE Endah Yuniarti
Jurnal Teknologi Dirgantara Vol. 17 No. 1 Juni 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.a3061

Abstract

This research studies influence of bird model on impact pressures during bird strike, namely Hugoniot and Stagnation pressure through initial modelling by numerical simulations using finite element method. Finite element simulation of bird strike have primarily modelled the bird as either a flat or hemispherically ended cylinder. The geometry is simulated with different L/D ratio, 1.4, 1.6, 1.8 and 2.0. Elastic-plastic hydrodynamic material model is used in simulation. Bird model simulation are using lagrangian method and initial velocities are 100, 200 and 300 m/s. Simulation results of hemispherically ended cylinder bird models show variation of L/D ratio provide Hugoniot pressure 10-19 times higher than stagnation pressure in L/D = 1.4, 8-18 times in L/D = 1.6, 9-17 times in L/D = 1.8 and 4-16 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2. As for cylindrical bird model show variation of L/D ratio provide Hugoniot pressure 35-38 times higher than stagnation pressure in L/D = 1.4, 30-47 times in L/D = 1.6, 31-52 times in L/D = 1.8 and 28-48 times in L/D = 2. The Hugoniot pressure shows a lower value at an L/D ratio of 1.4 and 1.6 compared to other ratios and the Stagnation pressure is higher at L/D ratio 2.
PEREDAM KEJUT DAN GETARAN BAGI MUATAN RX-250 Robertus Heru T.
Jurnal Teknologi Dirgantara Vol 6, No.1 Juni (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

akalah ini membahas perancangan dan pengujian sistem peredam kejut bagi payload RX-250. Sistem propulsi dari roket ini memberikan percepatan 12 g selama 12 detik, yang timbul (dan hilang) dalam tempo per-seribu detik. Beban tersebut, bersama dengan getaran yang timbul dari reaksi struktur roket terhadap beban aerodinamis dan stabilitas pembakaran, dapat mengakibatkan terjadinya kejut (shock) dan getaran yang merusak bagian sensitif dari payload elektronik. Untuk mencegah kerusakan pada payload elektronik, maka peredam kejut dan getaran yang terbuat dari pegas baja (wire type) dipasang antara roket dengan payload. Makalah ini membahas implementasi teknis perancangan yang meliputi uji darat dan uji terbang dari peredam tersebut yang pertama kali diadakan pada bulan Desember 2006.
ANALISIS TEKANAN STATIK ALIRAN DI PERMUKAAN PITOT STATIK TEROWONGAN ANGIN TRANSONIK LAPAN Agus Aribowo; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 5, No.2 Desember (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Static pressure stream analysis has been done on the surface of pitot static for LAPAN transonic wind tunnel by means of numeric and analytic methods. Static pressure hole is placed at 25 cm behind static pitot leading edge. Numerical analysis result demonstrates that shock wave begins to rise under free stream with velocity of 0.9 march. Shock wave occurs in an area around static pitot leading edge so the stream velocity around static pressure hole almost equal with free stream velocity. There is shock wave that cause decreasing of stream total pressure. By known the total pressure and streamn velocity around static pressure hole then static pressure can be calculated. Mach number in the test section can be known from pressure ratio. Keywords: Static pitot, Shock wave, Static pressure, Transonic.

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