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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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RANCANGAN DAN ANALISIS STRUKTUR SUDU TURBIN ANGIN LPN 10000 E Sulistyo Atmadi; Firman Hartono
Jurnal Teknologi Dirgantara Vol 3, No.2 Desember (2005)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2005.v3.a816

Abstract

Structure of the LPN 10000 E wind turbine blade has been manufactured and its structural analysis to find out the strenght of this structure during its operation has also been conducted. The method of aero bending moment and centrifugal bending moment and load has been used while neglegting frcitional and torsional load. The analysis is obtained for composite blade strengthened by high strength carbon unidirectional reinforcement composite. With safety factor of 1.3 minimum, it was concluded that the blade is strong enough to use at its designed operational load.
Front Pages JTD Vol 14 No 2 Des 2016 Redaksi Jurnal
Jurnal Teknologi Dirgantara Vol. 14 No. 2 Desember 2016
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Front Pages JTD Vol 14 No 2 Des 2016
SIMULASI CFD PADA DIFFUSER AUGMENTED WIND TURBINE (DAWT) : EFEK BENTUK INLET DAN PANJANG DIFUSER TERHADAP DISTRIBUSI KECEPATAN ANGIN DI EXIT DIFUSER [CFD SIMULATION IN DIFFUSER AUGMENTED WIND TURBINE (DAWT): EFFECT OF INLET SHAPE AND DIFFUSER LENGTH ON WIND SPEED DISTRIBUTION AT DIFFUSER EXIT] Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol.10 No.2 Desember 2012
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The objective of the research is to obtain a lighter diffuser design. It is done by modifications previously designed diffuser on the shape and length of its inlet. Thus the study analyze the effect of modified inlet and diffuser length on the distribution of wind speeds at the nozzle exit. Analysis was performed using a CFD-based software. Modifications was made to the diffuser inlet and exit diameter each-amounting to 4 and 2 m. Modified inlet can improve performance by 1.4%; meanwhile the wind angle of 60º, the performance was reduced by 2.45%, due to the separation. Shortening the length diffuser can reduce the velocity distribution in the exit, maximum of occurs at length of 1 m at 4.6%. Therefore it is recommended that optimum diffuser length is 2 m. Key words: Wind turbine, Diffuser, CFD
STABILITY AND CONTROLABILITY ANALYSIS ON LINEARIZED DYNAMIC SYSTEM EQUATION OF MOTION OF LSU 05-NG USING KALMAN RANK CONDITION METHOD Angga Septiyana
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.a3318

Abstract

This paper discusses the stability, control and observation of the dynamic system of the Lapan Surveillance UAV 05-NG (LSU 05-NG) aircraft equation. This analysis is important to determine the performance of aircraft when carrying out missions such as photography, surveillance, observation and as a scientific platform to test communication based on satellite. Before analyzing the dynamic system, first arranged equations of motion of the plane which includes the force equation, moment equation and kinematics equation. The equation of motion of the aircraft obtained by the equation of motion of the longitudinal and lateral directional dimensions. Each of these equations of motion will be linearized to obtain state space conditions. In this state space, A, B and C is linear matrices will be obtained in the time domain. The results of the analysis of matrices A, B and C show that the dynamic system in the LSU 05-NG motion equation is a stable system on the longitudinal dimension but on the lateral dimension directional on the unstable spiral mode. As for the analysis of the control of both the longitudinal and lateral directional dimensions, the results show that the system is controlled.
RANCANGAN DAN ANALISIS AERODINAMIKA SUDU TURBIN ANGIN KAPASITAS 300 KW Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 6, No.2 Desember (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Penelitian ini merupakan bagian dari kegiatan Perancangan SKEA 300 kW. Rotor dirancang dengan diameter 45 m dengan jumlah sudu tiga buah. Penampang sudu berbentuk airfoil NACA 4424, 4418, dan 4412 berurutan dari pangkal hingga ujung. Prestasi airfoil dihitung dengan simulasi secara CFD dengan mempertimbangkan efek bilangan Reynolds dan bilangan Mach. Geometri sudu mempunyai puntiran sebesar 15º. Dengan memperhitungkan rugi-rugi antara rotor dan generator, maka sudu akan mampu menghasilkan 350 kW pada kecepatan angin nominal 10 m/det dengan sudut pasang sudu sebesar 2º pada putaran 35 rpm dan tip speed ratio λ = 8,24.
ANALISA KEAKURATAN SENSOR SUHU ANALOG MODUL APRS SATELIT LAPAN-A2 DENGAN MENGGUNAKAN MODUL UJI VALIDASI (ANALISYS OF ANALOGUE TEMPERATURE SENSOR ACCURACY ON LAPAN-A2 SATELLITE APRS MODULE USING VALIDATION TEST MODULE) Andi Muhktar Tahir; Deddy El Amin
Jurnal Teknologi Dirgantara Vol. 12 No. 2 Desember 2014
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Modul Automatic Position Reporting System (APRS) merupakan salah satu muatan Satelit Lapan-A2 (Lapan-Orari), sebuah mikro satelit yang mempunyai misi penanggulangan bencana alam. Modul APRS yang digunakan oleh Lapan-A2 merupakan produk komersial sehingga perlu dilakukan pengujian thermal sebelum diluncurkan, terutama untuk mengukur keakuratan data dari sensor suhu analog yang terdapat di dalamnya. Pengujian thermal dengan menggunakan thermal chamber VC3 4018 terhadap sensor analog selain berfungsi untuk mengukur temperatur dari APRS itu sendiri dan suhu ruang di sekitarnya, pada dasarnya juga bertujuan untuk mengetahui daya tahan modul APRS terhadap perubahan suhu saat Lapan-A2 berada di orbit.Dengan meletakkan sebuah sensor suhu dijital secara berdampingan langsung dengan sensor suhu analog dalam modul APRS, proses pengujian di dalam thermal chamber berlangsung. Sebagai acuan untuk proses validasi kedua sensor suhu tersebut, dipergunakan data suhu yang diperoleh dari dua sensor suhu dijital yang diletakkan di dalam thermal chamber selama proses pengujian dan data ini diproses di dalam sebuah modul mikrokontroler yang diberi nama modul uji validasi sebelum dikirim ke modul APRS, sehingga nantinya data akhir dari keempat sensor suhu keluar bersamaan sehingga dengan mudah dapat langsung dibandingkan. Hasil akhir yang berupa grafik temperatur terhadap waktu menunjukkan bahwa dengan menggunakan rentang kesalahan ±1°C, sensor analog dari modul APRS kurang akurat dalam memberikan data terutama pada saat temperatur diatas 30°C.Kata kunci : APRS, Satelit Lapan-A2, Sensor suhu, Uji validasi
ANALISIS TEGANGAN PADA TABUNG KOMPOSIT SERAT KARBON UNTUK MOTOR ROKET BERDIAMETER 200 MM DENGAN METODE SINGLE LAYER LAMINATED ELEMENT Ronald Gunawan Putra,; Robertus Heru Triharjanto
Jurnal Teknologi Dirgantara Vol 8, No.2 Desember (2010)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

This research analizes rocket RWX 200 motor tube using carbon fiber reinforced for 6 mm thickness in order to optimize the weight. Carbon fiber is chosen due to its mechanical properties such as high strength and stiffness, and high temperature resistance, as the specification needs of the rocket motor tube. Rocket motor tube is manufactured by using weaving method, while the analysis and simulation is calculated by assuming it as laminate with the [0/90]s stacking sequence. From the calculation and simulation, it is determined that the X stress component of the laminates is below the strength of the material, while the Y stress component is beyond the strength of the material. It can be concluded that 900 laminae in each laminates has been failed. Keywords: Composite tube, Finite element method, Rocket motor
PENGARUH DIOCTYL ADIPATE TERHADAP SIFAT RHEOLOGIKAL HTPB TERPLASTISISASI (EFFECT OF DIOCTYL ADIPATE ON THE RHEOLOGICAL PROPERTIES OF PLASTICIZED HTPB) Afni Restasari; Luthfia Hajar Abdillah; Rika Suwana Budi; Kendra Hartaya
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.a3003

Abstract

Pengembangan pengetahuan terhadap sifat rheologikal isian cair dari propelan berguna untuk mendapatkan sifat slurry yang optimum. Pengembangan ini dapat dimulai dari campuran HTPB-DOA sehingga penelitian ini bertujuan untuk mengetahui pengaruh DOA terhadap sifat rheologikal HTPB-DOA yang meliputi sifat alir terhadap shear rate, viskositas dan viskositas saat zero shear rate. Dalam metodenya, DOA divariasi 0, 5, 10, 15 dan 20% dan dicampur dengan HTPB. Sifat rheologikal dipahami dengan mengukur viskositasnya pada kecepatan putar 0,5; 1; 1,5; 2; 2,5; 3; 4 dengan spindel tipe 2 dari viskometer Brookfield dan menganalisa grafik shear stress vs shear rate serta viskositas vs shear rate. Berdasarkan analisa tersebut, diketahui bahwa campuran HTPB-DOA bersifat shear thickening. Semakin banyak DOA yang ditambahkan, semakin rendah viskositas campuran, semakin rendah nilai viskositas pada zero shear rate dan semakin kuat sifat shear thickening dari campuran.
PENELITIAN TRANSMISIBILITAS ALAT PEREDAM GETARAN PADA MUATAN ROKET RX 550 LAPAN (RESEARCH TRANSMISSIBILITY OF VIBRATION DAMPERS EQUIPMENTS ON ROCKET RX 550 LAPAN) Agus Budi Djatmiko
Jurnal Teknologi Dirgantara Vol. 15 No. 2 Desember 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.v0.a2497

Abstract

Every single piece of structural engineering as well as the rocket payload, has its mass and elasticity, and also has the potential to cause vibration. In general, the occurrence of vibration in the engineering structure is not desirable. Therefore, to the extent possible the vibrations is arranged to be muted. Acceleration nuisance caused by the combustion process in rocket can cause vibrations with a large amplitude resulting in damage to the structure of the mutant rockets and electronic equipment that is in charge of the rocket could not work as intended, based on the experience of electronic equipment will be damaged if the acceleration bully at 10 g that work on the rocket is not reduced, it is designed for a vibration damping apparatus, equipment consisting of springs and dampers are arranged such that a damping effecton the vibration occurs.In this research used springs with stiffness k = 120,000 N/m, damping factor = 0.0503 and mass of charge (m) = 10.5 kg, with acceleration of 1 G and working frequency from 0 to 2000 Hz. Interest transmissibility research on tool vibration dampers is to determine the magnitude of the acceleration is transmitted to the rocket payload. The results of the dampening experiment, at the beginning of acceleration or G force transmitted to a rocket load of 1 g or TR = 1, but after passing a resonance or obtained G force transmitted to a rocket payload of  0,1 g or TR = 0.1 (the silencer is good enough). From the results of this study can be said that the silencer can be used to reduce vibration on the rocket payload RX 550. AbstrakSetiap struktur rekayasa seperti halnya pada muatan roket, mempunyai massa dan elastisitas, maka struktur tersebut mempunyai potensi untuk menimbulkan getaran. Pada umumnya terjadinya getaran pada struktur rekayasa adalah tidak diinginkan, oleh karena itu sedapat mungkin getaran tersebut diusahakan untuk diredam. Percepatan pengganggu yang ditimbulkan oleh proses pembakaran pada roket dapat menyebabkan getaran dengan amplitudo yang besar yang mengakibatkan kerusakan  pada struktur mutan roket dan alat elektronik yang ada pada muatan roket sehingga tidak dapat bekerja seperti yang diinginkan. Berdasarkan pengalaman, alat elektronik akan mengalami kerusakan jika percepatan pengganggu sebesar 10 g yang bekerja pada roket tidak direduksi. Untuk itu dirancang suatu alat peredam getaran, peralatan tersebut terdiri dari pegas dan damper atau peredam yang disusun sedemikian rupa sehingga muncul efek redaman terhadap getaran. Pada penelitian ini digunakan pegas dengan kekakuan k = 120.000 N/m, faktor redaman  = 0,0503 dan massa muatan (m) = 10,5 kg, dengan percepatan sebesar 1 G dan frekuensi kerja dari 0 sampai dengan 2000 Hz. Tujuan penelitian transmisibilitas pada alat peredam getaran ini adalah untuk mengetahui besarnya percepatan yang ditransmisikan ke muatan roket. Hasil penelitian alat peredam, pada saat awal percepatan pengganggu atau G force yang ditransmisikan ke muatan roket sebesar 1 g atau TR = 1, tetapi setelah melewati resonansi atau  didapat G force yang ditransmisikan ke muatan roket sebesar  0,1 g atau TR = 0,1 (alat cukup baik). Dari hasil penelitian ini  dapat  dikatakan bahwa alat peredam dapat digunakan untuk meredam  getaran pada muatan roket RX 550.
EMISI RADIASI MEDAN ELEKTROMAGNETIK KABEL KOMUNIKASI BROADBAND Sumarni Mardjoeki
Jurnal Teknologi Dirgantara Vol 2, No.2 Desember (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.a802

Abstract

Broadband communication technology transmits data in high speed. Broadband communications using aerial cable as its transmission medium, will radiate electromagnetic field into its surrounding environment. The radiated electromagnetic field is a potential source of interference, especially with other frequency radio devices, which are operated in the same frequency range. In this case, the long wires carrying broadband signals will generate a radio frequency electromagnetic emission. This paper makes a study about interference from the xDSL (Digital Subcriber Line) communication broadband signals, which using an existing telephone subscriber loop cable network as its transmission medium. Generally, the subsciber loop cable is an aerial cable. In order to make the radiation influence does not impact the other radio equipment performance, the standard CISPR 22 regulates the limits, which are 35 dBuV (average) at a distance of 30 for Class A (industrial) equipment and at a distance of 10 m for Class B (residential) equipment.

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