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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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Front Pages JTD Vol 17 No.1 Juni 2019 Redaksi Jurnal
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.a3151

Abstract

ANALISIS DESAIN WHEEL DRIVE ELECTRONIC (WDE)–LAPAN UNTUK PENGEMBANGAN SATELIT LAPAN-A2 Gunawan S Prabowo; Hasan Mayditia; Arbai Yusuf
Jurnal Teknologi Dirgantara Vol 7, No.1 Juni (2009)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Wheel Drive Electronic (WDE) merupakan komponen terpenting dalam sistem kontrol Attitude satelit-mikro. Sub-sistem ini menjadi salah satu pilihan strategis LAPAN untuk tahap pengembangan dan penguasaan teknologi satelit-mikro selanjutnya, khususnya penguasaan pada level sub-sistem secara mandiri. WDE terdiri dari komponen hardware dan software terintegrasi, yang mampu mengatur output torsi dan momentum sudut dari inersia flywheel, baik secara independen (open loop) maupun close loop dengan input sensor gyro. Bersama dengan flywheel dan gyro, WDE menyusun sebuah sistem reaction wheel yang mampu memberikan kestabilan orientasi posisi dan kecepatan sudut pada salah satu sumbu satelit. LAPAN telah berhasil mengembangkan satu unit WDE sebagai WDE yang pertama dan akan diujiterbangkan bersama satelit LAPAN-A2.
EFEK DEFLEKSI PADA SUDU TURBIN ANGIN TERHADAP KELUARAN DAYA Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 4, No.1 Juni (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The type of material used in the fabrication of wind turbine blade is a very important factor so that it will not exceed the allowable maximum deflection. An analysis is conducted to study this deflection effect to that power output and as case study, a 7.6 m blade of 10 kW LPN 10000 E turbine is used. Several assumption as such as deflection due to wind speed at perpendicular to local plane local blade are diameter blade and direction of aerodynamic at aerofoil plane local blade are considered. The distribution of blade deflection along the twisted span is assumed uniform. Calculation is performed for the polynomial order of 2,3 and 4, with variety of deflection of 0.2 m, 0.5m, 1 m and 1.5 m. for design wind speed of 9 m per s it was found that for 0.5 deflection, the losses of 6 percent, 9 percent and 12 percent for blade shape polynomial order 2,3 and 4 consequentively are produced; whereas for 1.5 m deflection, losses are 46 percent, 53 percent, and 56 percent for the same polynomial shape. If a maximum loss of 10 percent is taken, then the max allowable deflection is 0.5 m. Keywords: Defleksi, Sudu, Turbin angin, Keluaran daya, Rugi-rugi.
Front Page JTD Vol. 13 No. 1 Juni 2015 Redaksi Jurnal
Jurnal Teknologi Dirgantara Vol.13 No. 1 Juni 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Front Page JTD Vol. 13 No. 1 Juni 2015
METODE TRACKING KECEPATAN ROKET MENGGUNAKAN TRANSPONDER DOPPLER DUA-FREKUENSI (ROCKET SPEED TRACKING METHOD USING TWO-FREQUENCY DOPPLER TRANSPONDER) Wahyu Widada
Jurnal Teknologi Dirgantara Vol.11 No.1 Juni 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Sistem Doppler tracking untuk roket biasanya hanya menggunakan satu frekuensi pembawa. Tulisan ini membahas sebuah metode Doppler radio pelacak roket dengan menggunakan dua frekuensi gelombang radio. Sistem ini menggunakan transponder Doppler pada frekuensi 465 MHz dan 2400 MHz secara simultan. Radio frekuensi rendah digunakan untuk mengukur kecepatan-tinggi roket dan sebaliknya gelombang radio frekuensi lebih tinggi digunakan untuk mengukur kecepatan rendah roket. Hasil yang diperoleh dari metode ini lebih akurat 5.4 kali pada kecepatan kurang dari 0.7 Mach dibandingkan dengan hasil dari sistem Doppler yang menggunakan hanya satu frekuensi radio. Metode ini cocok untuk mengukur kecepatan roket hingga 3.8 Mach.Kata kunci: Doppler tracking, Roket, Dua-frekuensi, Resolusi tinggi, Transponder
Effect of Isomer Composition of Hydroxy Terminated Polybutadiene (HTPB) in Low Shear Flow Behavior (Efek dari Komposisi Isomer dari Hydroxy Terminated Polybutadiene (HTPB) terhadap Sifat Alir dalam Geseran Rendah) Afni Restasari; Luthfia Hajar Abdillah; Retno Ardianingsih; Rika Suwana Budi
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.a3341

Abstract

HTPB is the ultimate component of matrix builder for high-filled composite materials. Flow behavior of HTPB in low shear is crucial in casting the composite. Considering the characteristics of hydrocarbon, this work aims to investigate the effect of microstructure composition of HTPB on its flow behavior. In this work, HTPB with different composition of 1,4-cis, 1,2-vinyl and 1,4-trans microstructures were used. Fourier-Transform Infra-Red spectroscopy (FT-IR) was used to determine the composition. It was calculated as a ratio of peak area of 710, 910 and 970 cm-1 for 1,4-cis, 1,2-vinyl, 1,4-trans isomers respectively. Viscosity was measured using a rotational viscometer at various low shear rates. It is found that HTPB with high 1,2-vinyl/1,4-trans isomers shows shear thickening behaviour, distinguished significantly from Newtonian flow of the others. It is suggested that mechanism of shear thickening involves a certain configuration of 1,2-vinyl and 1,4-trans isomers that builds different degrees of flow resistance from one to other shear layers. The configuration and flow resistance changes among layers as shear increases.
RANCANGAN MISI LAPSAT-2 FM - Adrianti P.S.; Eriko Nasser; Andi Mukhtar; Gunawan Setio Prabowo; - M.Mukhayadi
Jurnal Teknologi Dirgantara Vol 1, No.1 Juni(2003)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Now adays, itis widelly used the term Nano-satellite when we refer to those satellites whose mass less than about 10 kg. The design of LAPSAT-2 FM has weight more than 10 kg and less then of 15 kg but we consider as a nano-satellite continuing the previous design LAPSAT-1, This satellite designed as technology demonstrator, carrying store-and forward communication and remote sensing missions. Satellite build together with Malaysia in a same mission in parallel separately. This paper, discussed about mission definition and analysis referring to orbit, payload, budget and launch alternative and also mission operation.
ANALISA SENSITIVITAS PADA DESAIN AWAL SATELIT MIKRO PENGAMAT BUMI (SENSITIVITY ANALYSIS ON PRELIMINARY DESIGN OF EARTH OBSERVATION MICRO-SATELLITE) Robertus Heru Triharjanto; Ridanto Eko Poetro; Hari Muhammad
Jurnal Teknologi Dirgantara Vol.11 No.1 Juni 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Makalah ini membahas analisa sensitivitas pada proses desain satelit mikro pengamat Bumi. Tujuan dari analisa ini adalah untuk melihat parameter input desain yang paling mempengaruhi kinerja satelit. Jenis satelit yang menjadi batasan dalam riset ini adalah satelit kelas hingga 100 kg dengan batasan dimensi untuk peluncuran sebagai muatan tambahan (auxilary payload). Misi pengamatan Bumi yang dimaksud juga dibatasi pada misi yang menggunakan sensor optik (multispectral imager), dimana kinerja utamanya adalah resolusi dan jumlah spektrum. Proses desain yang dimaksudkan dalam riset ini dibatasi hingga desain awal (preliminary design) dengan beberapa asumsi yang didasari oleh data empiris. Hasil analisa menunjukkan bahwa resolusi sangat berpengaruh pada jumlah data yang harus diproses terutama untuk resolusi tinggi, sehingga berefek pada jumlah daya listrik yang dikonsumsi. Resolusi, yang merupakan fungsi ukuran lensa juga berpengaruh pada berat satelit yang harus mengakomodasi dimensinya. Pada sisi lain, akomodasi lensa berakibat pada bertambahnya jumlah daya listrik yang bisa dihasilkan oleh subsistem daya satelit. Sementara jumlah spektrum juga berpengaruh terhadap parameter batasan satelit, yakni berat dan konsumsi daya, namun lebih moderat.Kata kunci: Desain Satelit mikro, Satelit pengamat bumi, Analisa sensitivitas
DESAIN ALAT UJI NOSEL DENGAN MENGGUNAKAN PRINSIP TEROWONGAN ANGIN SUPERSONIK Bagus H. Jihad; Dedi Priadi
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 The accuracy of nozzle design can be improved by validation. Two methods of validation is software or hardware application. The software can be either CFD software or special software for the nozzle design, such as NOZZLE ® or Aerospike ®. The limitations of CFD software is on unsteady flow conditions. while the limitations of special software is the obscurity of assumptions used. Therefore, the flow validation experimental is important to be implemented. Lapan has three units of wind tunnels, namely subsonic, transonic and supersonic. They have the capability to measure the external flow of the body. While the nozzle design purpose is mostly to investigate the internal flow of the nozzle. Therefore, the nozzle flow testing system which is called a mini wind tunnel has been designed.This wind tunnel is designed to have speed of Mach 2.4, but the effective speed of 2 Mach. By using a calculation we obtain the run time of 46 seconds. If we assume the pressure drop is 40%, then actually the run time is 28 seconds.Keyword:Windtunnel, Nozzle, Supersonic, Run-time, Schlieren
FINITE ELEMENT MODELING OF LAPAN-A5/CHIBASAT DEPLOYABLE SOLAR PANEL COMPOSITE PLATE Robertus Heru Triharjanto, M.Sc; Poki Agung Budiantoro
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.a3065

Abstract

LAPAN-A5/ChibaSat, that will carry synthetic aperture radar payload, requires a lot more power generation capacity, compared to its predecessor. Therefore, its solar panel will be deployed in orbit to ensure maximum sun exposure. Since the deployable system requires solar panel plate that lightweight and strong, honeycomb composite material is selected. The selection of such material requires special treatment in the satellite structural stiffness calculation. The objective of the research is to find simple stiffness model of the plate, so that later it can be integrated with the total satellite structural model and used by launch authority in its total vehicle modal analysis. The modeling used finite element software, and the simplified honeycomb model is validated using standar plate stiffnes problem. After model validation, the boundary condition as in the LAPAN-A5/ChibaSat deployable system is imposed. The result shows that the stiffness of the deployable solar panel plate has met the launch requirement of PSLV’s auxiliary payload. Therefore, the design mode can be used in the development of LAPAN-A5/ChibaSat.  

Page 20 of 34 | Total Record : 333

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