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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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RX-320 Rocket Static Pressure Combustion Chamber Prediction and Validation by Using Invers Method Sofyan Sofyan; Vicky Wuwung
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.a2866

Abstract

The static pressure data of the combustion chamber which can generally be obtained by performing direct measurements when static test is performed on the rocket is an important parameter in predicting the thrust and design of the combustion chamber of the rocket. However, there is a model rocket for flight test that is used in static test. Thus, there is no mounting for static pressure sensors (for measurement) are made. To solve the problem, then the inverse method is used as an iterative solution for the basic equations of the rocket thrust force in the nozzle by guessing the value of the static pressure of the combustion chamber firstly and calculate the iteration by including the value of the rocket thrust from static test data and the efficiency variation of the nozzle. The results of this calculation are then validated by using a 3D-CFD numerical simulation to obtain a more detailed comparison on the nozzle. In this research RX 320 LAPAN rocket nozzle with focus on maximum static thrust data of static test results is used. The 3-D numerical simulation is performed using Numeca CFD software, with k-extended wall extended turbulent model, numerical multigrid level 3 scheme, center based, and convergence criteria of 10 e-05. The result of calculation by inverse method and its comparison with numerical simulation shows that the smallest difference of the combustion chamber static pressure between inverse method and numerical simulation is 0.017%, that is achieved at 92% nozzle efficiency. At this point, the static pressure of the combustion chamber is 57.94 bar. From this point of view, the results of this comparison indicate that the inverse method can be used accurately for static pressure of the combustion chamber prediction, if the nozzle efficiency is given correctly. Furthermore, with given static pressure of the combustion chamber correctly, it will be very helpful in the design of the more optimum combustion chamber.
PENGARUH PELARUT (ETIL BENZENA), PERBANDINGAN STYRENE BUTADIENE RUBBER (SBR) TERHADAP STIREN, DAN JUMLAH INISIATOR (BPO) PADA PEMBUATAN HIGH IMPACT POLYSTYRENE (HIPS) Dwi Wahyuni
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.a800

Abstract

High impact polystyrene (HIPS) is the widely used material now, and also for the aerospace material as a communication instrument system and an electrical insulation. In order to produce HIPS, there are a view method which can be executed. In this case, the research is executed by the copolymerization processes of styrene butadiene rubber (SBR) solution in styrene. Variables which influence to the result properties (HIPS) are the SBR to styrene ratio, the solvent (ethyl benzene), the benzoyl peroxide initiator (BPO). The properties of the product are tensile strength, impact strength, softening point, melting point and the hardness. The result showed that the properties of the HIPS product was near of the HIPS high heat. The optimal processes condition was the solvent to the styrene monomer ratio was 0.05492, the SBR to the styrene ratio was 0.1236 and the BPO to the styrene ratio was 0,0003. The properties of the HIPS product were: the impact strength was (519-1215) N per cm, the tensil strength not more than was 106 N per cm, the elongation was (36-54) percent and the hardness was (65-69) shore A. This properties achieved at the mixing polymerization processes 4 scale in 11-12 hours, the early mixing at 4 scale 1 hours, the cutting chain 2 drops.
RANCANGAN SISTEM ORIENTASI EKOR TURBIN ANGIN 50 KW Sulistio Atmadi; 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

A fin orientation system for wind turbine with a maximum capacity of 50 kw has been designed. The fin system is designed with for the yawing motion. The method used is based on the moment equilibrium criteria. Eccentricity distance of 10 cm was selected for the design. The location of the fin control is placed at the connection between the generator and the fin bar. The design procedures a fin bar of 6m, with the fin area of 25 m. The center of the fin force is located at 3 m from the nose. Whereas the fin angle to the center of the turbine axis is 21.9 degrees. Keywords: Wind turbin, fin, oreintation.
APLIKASI CFD DALAM PENENTUAN PERFORMA MESIN TURBOFAN MODEL CFM56-5B YANG MENGALAMI CACAT PADA KIPAS UNTUK KEPUTUSAN MAINTENANCE Vicky Wuwung; Puspa Wandani; Carolus Bintoro
Jurnal Teknologi Dirgantara Vol. 14 No. 1 Juni 2016
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar | DOI: 10.30536/j.jtd.2016.v14.a2945

Abstract

This paper deals with the study of damage assessment that occurred on the fan blade of turbofan engine CFM 56-5B. The damage requires a maintenance decision, whether a fan blade is still capable to be used or needs to be repaired/replaced. Although regulations stipulate that such damage is still acceptable, but it should be studied in terms of performance, whether the fan still can give a good performance or not. The study was conducted by simulating CF M56-5B on CFD-Numeca software with the fan blade in good and defects conditions. The defects on all the blade is a dent lies on 70% span blade with 0.069” depth on the leading edge to simulate the damage caused by a bird strike. In Numerical simulation, the flow is modeled steady and Spallart- Almaras turbulent model is used . Numerical simulation result show engine performance is reduced in take-off condition for 14% for thrust and 16% for efficiency, and 55% for thrust and 54% for efficiency for cruise condition. This engine performance reduction in take-off condition based on AC 25-13 regulation is definitely save and there is no need of repair or replacement action. Meanwhile, for cruise condition, this engine performance reduction means much higher fuel consumption although safe condition is reached. Thus, based on AC 25-13, engine performance reduction in this case leads to a maintenance decision of no need to repair or replacement action. ABSTRAKPenelitian ini membahas mengenai kajian kerusakan yang terjadi pada bilah kipas mesin turbofan CFM56-5B. Kerusakan tersebut memerlukan adanya sebuah keputusan maintenance, apakah bilah kipas tersebut masih layak digunakan ataukah perlu di repair atau diganti. Meskipun regulasi menetapkan bahwa kerusakan tersebut masih dapat diterima, namun perlu ditinjau dari segi performanya, apakah kipas masih dapat memberikan performa yang baik atau tidak. Kajian dilakukan dengan menyimulasikan model bilah kipas CFM56-5B pada kondisi baik dan cacat pada perangkat lunak CFD-Numeca di kondisi take-off dan cruise. Cacat pada bilah berupa dent dengan kedalaman 0.069” dan terletak seragam di semua bilah pada 70% span bilah di bagian leading edge sebagai simulasi kerusakan akibat adanya bird strike. Simulasi numerik dilakukan dengan kondisi pemodelan aliran steady, dan menggunakan model turbulen Spallart-Allmaras. Hasil simulasi numerik menunjukkan adanya penurunan performa mesin pada Thrust di kondisi take-off sebesar 14% dan penurunan efisiensi sebesar 16%, sedangkan pada kondisi cruise, penurunan Thrust dan efisiensi berturut-turut adalah sebesar 55%, dan 54%. Penurunan Thrust pada saat take-off berdasarkan regulasi AC 25-13 adalah aman dan tidak perlu dilakukan repair atau replacement. Namun, meskipun aman, mesin akan boros bahan bakar ketika berada dalam kondisi cruise sehingga perlu dilakukan repair atau replacement. Penentuan keputusan maintenance jika didasarkan pada regulasi AC 25-13 pada akhirnya adalah tidak diperlukannya repair atau replacement pada bilah kipas.
DESAIN DAN PENGUJIAN STRUKTUR SATELIT MIKRO LAPAN-TUBSAT Robertus Heru Triharjanto
Jurnal Teknologi Dirgantara Vol 4, No.2 Desember (2006)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The paper discuss about the design and test of the structure of LAPAN-TUBSAT micro-satellite, which is the task done by the writer during his time as the member of LAPAN-TUBSAT integration and test. The discussion includes the design requirment for the structure as mechanical interface and its implementation as well as its design validataion process via test as accordance to the requirement set by the launcher authority. Keywords: Satelit mikro LAPAN-TUBSAT.
Back Pages JTD Vol 15 No 1 Juni 2017 Redaksi Jurnal
Jurnal Teknologi Dirgantara Vol. 15 No. 1 Juni 2017
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Back Pages JTD Vol 15 No 1 Juni 2017
KAJIAN RADIUS OPERASIONAL PESAWAT TEMPUR DI ATAS WILAYAH TERITORIAL REPUBLIK INDONESIA (STUDY ON RADIUS OF ACTIONS FOR FIGHTER JETS OVER THE ALL INCLUSIVE TERRITORY OF REPUBLIC OF INDONESIA) Rais Zain; Ika Suwarni
Jurnal Teknologi Dirgantara Vol. 11 No.2 Desember 2013
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Sebagai suatu negara kepulauan, wilayah Indonesia terdiri dari ribuan pulau yang tersebar disekitar garis khatulistiwa yang kedaulatannya berbentuk Negara Kesatuan Republik Indonesia. Konsekuensinya adalah tantangan untuk menjaga kedaulatan teritorial dari ancaman asing menjadi lebih kompleks. Untuk itu maka dikaji beberapa korelasi antara penggunaan jumlah landasan udara dan nilai minimum dari radius operasional (radius of action). Pada makalah ini dibuat lima skenario yang mengkombinasikan pangkalan udara yang dikelola oleh TNI-AU, TNI-AD, TNI-AL, dan yang diusulkan penulis. Skenario pertama hanya melibatkan pangkalan TNI-AU yang sudah mengoperasikan pesawat tempur. Skenario kedua adalah Skenario pertama ditambah dengan pangkalan yang sudah masuk kedalam rencana pengembangan TNI-AU. Skenario ketiga adalah Skenario kedua ditambah dengan pangkalan usulan penulis. Sedangkan Skenario keempat adalah Skenario ketiga dikurangi dengan pangkalan yang fungsinya tumpang tindih dalam hal radius operasional. Yang kelima adalah Skenario kedua ditambah dengan pangkalan udara yang dikelola oleh TNI-AD dan TNI-AL. Hasil dari Skenario pertama menunjukkan bahwa radius operasional yang terbesar adalah 2400 Km yang berarti tidak mampu dicapai oleh pesawat Sukhoi Su-30. Sedangkan untuk Skenario keempat dihasilkan radius operasional yang dibutuhkan sebesar 554 Km, dimana nilai ini sudah mampu dicapai oleh prestasi terbang pesawat tempur IF-X / KF-X. Kata kunci: Teritoral Indonesia, Zona Pertahanan Udara, Pesawat Tempur, Radius Operasional
PENELITIAN PEMBUATAN POLI METIL METAKRILAT Dwi Wahyuni; Sri Rukmini Dewi
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.a781

Abstract

The poly methyl methacrylate (PMMA) research has been excecuted. Methyl methacrylate is polymerized by the free radical inisiation with the suspension condition using benzoyl peroxyde inisiator, water as a solution and the gelatine stabilizer, in this reseaarch is executed as a standard ratio (part per part:monomer : water : stabilizer = 100 : 350 : (0.1 1) with the inisiator to monomer ratio variation (part per part) are: 0.1 per 50; 0,175 per 50; 0,25 per 50; 0,25 per 50, the temperature variation are : 30 degree C, 45 degree C, 60 degree C and the time polymerization until 320 minutes. The result showed that the optimum monomer polymerizeation was at the inisiator to monomer ratio 0,25 per 50, the temperature at 45 degree C and at the time polymerization until 300 minutes with the monomer conversion was 86 percent. The Infra Red Spectroscopy analyses showed that there are poly methyl methacrylate in the product. The Gas Liquid Chromatography analysis showed the evolution of the monomer (methil methacrylate concetration.
RANCANG BANGUN ENJIN ROKET CAIR DENGAN GAYA DORONG 1000 KGF MENGGUNAKAN PROPELAN ASAM NITRAT – KEROSEN (DESIGN OF LIQUID ROCKET ENGINE WITH 1000 KGF THRUST USING NITRIC ACID – KEROSENE PROPELLANT) Arif Nur Hakim
Jurnal Teknologi Dirgantara Vol.13 No. 1 Juni 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

Enjin roket cair bergaya dorong maksimum 1000 kgf dengan pendinginan regenerative menggunakan fuel telah dirancang sebagai langkah awal untuk menjawab kebutuhan sistem propulsi roket yang memiliki impuls spesifik yang lebih tinggi, waktu pembakaran yang lebih lama dan kemampuan kontrol untuk Program Roket Pengorbit Satelit. Enjin didesain menggunakan pasangan asam nitrat dan kerosen avtur masing-masing sebagai oksidator dan fuel dengan sistem pengumpan gas inert bertekanan untuk mendorong propelan ke ruang bakar. Untuk mendistribusikan propelan, enjin mengadopsi injektor tipe impinging stream dengan 3 jet asam nitrat menabrak 1 jet kerosene yang dikelilinginya. Uji subsistem dilakukan untuk mengetahui kinerja masing-masing komponen enjin, sedangkan uji bakar dilakukan untuk mengetahui kinerja enjin secara keseluruhan. Hasil pengujian menunjukkan bahwa enjin ECX1000H2 dengan injektor konfigurasi kedua dapat menghasilkan semburan gas hasil pembakaran yang lurus dan cukup stabil dengan thrust rata-rata sebesar 610 kgf dan maksimum 670 kgf. Rendahnya thrust disebabkan oleh konfigurasi injektor yang masih belum optimal dan kecepatan suplai gas pendorong yang tidak cukup untuk membuat dorongan maksimum.Kata kunci: Enjin roket cair, Injektor, Asam nitrat, Kerosen
PERHITUNGAN DAN ANALISIS LOSSES, DIAMETER EFEKTIF ROTOR, DAN PENYERAPAN DAYA DAN ENERGI PADA DIFFUSER AUGMENTED WIND TURBINE (DAWT) Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 9, No. 2 Desember (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

The use of diffuser in wind turbine (DAWT) is aimed at increasing the effective speed to produce a higher power. A bigger and heavier turbine results in difficulty in manufacturing the turbine orientation system. This research consists of three parts i.e. the calculation and analysis of the losses, determination of the effective diameter of the rotor, and the calculation and analysis of the absorbed energy by DAWT. The losses calculation and analysis is based on the friction between the airflow and wall. The diameter of the rotor is choosen in the diffuser area which has minimum turbulence flow produced by the wind angle. The calculation and analysis of the power is based on its rotor diameter. Then the power converted to become energy. In this research, DAWT is assumed to have no orientation system so that easily manufactured, i.e. the rotor is oriented at a single direction. Wind direction and frequency is selected in three configurations. In the first configuration, the wind direction comes from all the twelve wind source direction with the same frequency in the 24 hour period, producing 2 hourly periods for every wind direction. In the second configuration, wind from 90° and 270° or perpendicular to the axial turbine axes are eliminated, and hence producing 10 different wind directions at 2.4 hourly periods. In the third configuration, the turbine is set at the beach whereby the wind direction comes only at two direction; the sea and land wind directions. At these conditions, the wind is assumed to come at 0°, 30°, 150°, 180°, 210°, and 330°. The aim of this research is to calculate the energy absorption of the wind rotor, and comparing with those produced without the diffuser system in place. In this research, a 2m rotor diameter and 4m diffuser diameter is selected, power coefficient of 0.3, wind speed of 5m/sec, and these parameters are constant for the 24 period under analysis. The result of the calculation shows that there are losses near wall especially for high wind angle. The rotor diameter have chossen about 1,940 m. The energy absorption of the wind rotor without the diffuser is 6.231 kJ. The energy absorption values for the 1st, 2nd and 3rd configuration with the diffuser produce 54.361, 65.234, and 101.316 kJ respectively. It shows that the use of diffuser in the wind rotor could produce an increase of up to 9 to 16 times in the power absorption of the rotor. Keywords: Wind turbine, DAWT, Electrical energy, Losses

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