cover
Article Per Year (5 Year)
All
Home Page
OAI Link
Editorial Team
Contact
Reviewer
Google Scholar
Contact Name
Heri Budi Wibowo
Contact Email
heribw@gmail.com
Phone
+6221-4892802
Journal Mail Official
jurnal.lapan@gmail.com
Editorial Address
Jl. Pemuda Persil No. 1 Rawamangun, Jakarta Timur 13220
Location
Kota adm. jakarta timur,
Dki jakarta
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
 2   3   4   5   6 
DEPARTURE TRAJECTORY OPTIMIZATION FOR NOISE ABATEMENT PROCEDURE IN SOEKARNO-HATTA INTERNATIONAL AIRPORT Vincentius N.S. Suryo; Benedikt Grüter; Johannes Diepolder; Neno Ruseno; Florian Holzapfel
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.a3376

Abstract

Air traffic noise emission has been a growing concern for communities living within the vicinity of airports due to a massive increase in air traffic volume in recent years. This work focuses on the noise annoyance problem by optimizing one of the RNAV trajectories, which aims to minimize the noise footprint of a flying aircraft in a low altitude trajectory. Optimal control theory is applied to minimize the number of awakenings caused by a departing aircraft while constraining the relative increase of fuel consumption with regard to a fuel-minimal trajectory. The aircraft simulation model is based on the BADA 3 database, while the noise is modeled according to the ANP database, both published by EUROCONTROL. The methodology is demonstrated for the Soekarno-Hatta International Airport (CGK) in Jakarta; the result shows the comparison between fuel-minimal trajectories and noise-minimal trajectories for seven aircraft types representing the fleet mix at CGK. The number of awakenings of the noise-minimal trajectories is reduced by 30.33%, with an additional of 5% fuel consumption for the seven aircraft types when compared to the fuel-minimal trajectory.
PENGEMBANGAN POLIURETAN BERBASIS CPO SEBAGAI LINER ADHESIVE - Heri BW; - Henny S; - Geni R
Jurnal Teknologi Dirgantara Vol 1, No.1 Juni(2003)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

In effort to increase the economic value of CPO (Crude Palm Oil), a research to use it as polyurethane raw material for the liner adhesive has been conducted. In order to get monoglyceride, CPO is glycerolized with glycerol, KOH is used as a catalyst and Pyridine solvent at 105 degree C for 4-8 hours. In the presence of isocyanate, such as TDI (Toluen Diisocyanate) monoglyceride as a diol becomes Polyurethane. Based on the adhesive strength test, this polyurethane polymer, produce a low conductivity and heat resistance up to 400 degree C(better quality compared with polyurethane to be used available in the local market). Therefore the polyurethane with CPO base a good potential material as a liner adhesive.
DESAIN DAN PENGUJIAN INTAKE KONIKAL SISTEM PROPULSI RAMJET PADA KECEPATAN SUPERSONIK (DESIGN AND TEST OF CONICAL INTAKE OF RAMJET PROPULSION SYSTEM AT SUPERSONIC SPEED) - Sofyan; Romie Oktovianus Bura
Jurnal Teknologi Dirgantara Vol.13 No. 1 Juni 2015
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Riset ini bertujuan untuk mendesain intake supersonik untuk aplikasi sistem propulsi ramjet. Desain intake ramjet sangat penting bagi proses pembakaran dalam ruang bakar mesin ramjet. Dalam desain intake konikal ini, kondisi Mach 2 dijadikan sebagai acuan, dengan kompresi eksternal. Penelitian ini juga menguji intake ramjet dalam terowongan angin supersonik. Desain dilakukan dengan menempatkan gelombang kejut pada bibir cowl intake untuk memperoleh pressure recovery yang tinggi dan gaya hambat serendah mungkin. Hasil desain analitik dibandingkan dengan hasil numerik pada berbagai kondisi intake – subkritikal, kritikal, dan superkritikal. Hasil numerik juga divalidasi dengan eksperimen model. Intake yang didesain memberi pressure recovery sebesar 0,93, namun hasil ini cukup berbeda dengan hasil eksperimental. Ini disebabkan karena efisiensi kompresi tidak diikutkan dalam proses desain.Kata kunci: Intake supersonik, Ramjet, Pressure recovery, Rasio laju massa
SIMULASI PENGGUNAAN DIFFUSER PADA TURBIN ANGIN SUMBU HORISONTAL UNTUK KENAIKAN DAYA Sulistyo Atmadi; Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

 One technique to improve the power output of a wind turbine is by implementing a diffuser, which is called the diffuser augmented wind turbine (DAWT). The area ratio between the inlet and outlet of the diffuser increases the flow rate inside the diffuser which in effect produces higher output power. In this research, a 2 meters rotor diameter was used. Diffuser diameter ratio variation of 2, 3, 4, and 5 were chosen which provides inlet diameter of 4, 6, 8, and 10 meter respectively. Power rotor coefficient is assumed to be constant of 0.30. Air speed distribution inside the diffuser is calculated using CFD method. The inlet speed to the diffuser is varied to give 4 different speeds. The wind angle at the inlet is also varied at 0º, 30º and 60º. The simulation result showed that at 0 degree angle, diffuser diameter ratio variation of 2, 3, 4, and 5 will increase the power output about 58, 622, 3169, and 11519 times respectively. It also showed that the increase in the output power for diameter diffuser ratio of 2 at 0º and 60º angle is 58 and 4 times respectively. Keywords:Wind turbine, Diffuser, CFD
IN-ORBIT IMPLEMENTATION OF ERROR PATCHING METHODS FOR LAPAN-A3/IPB OBDH FIRMWARE SYSTEM Muhammad Taufik; Wahyudi Hasbi; Abdul Karim
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.a3012

Abstract

ABSTRACTOBDH (On-board data handling) is a satellite subsystem that receives, processes, decides and executes commands from and to satellites. OBDH is built on two systems namely hardware and software integrated system (firmware system). In terms of hardware, OBDH uses a processor with 32bit RISC architecture, 128/256 Kbyte internal memory and a firmware system that is built using primitive programming. This programming uses the super loop architecture program and interrupt to manage the system to function properly. Problems occur when an error occurs in one of the functions in the interrupt routine resulting in failure of interpretation of commands or data from satellite sensors. This paper describes the implementation of the error patching methods on the LAPAN-A3/IPB Satellite OBDH firmware system in order to keep the system working well. Initial verification through testing on the ground have been successfully performed using engineering model of OBDH and hardware in the loop simulators (HWIL) module. Based on the test results, implementation on satellite has also been successfully done.ABSTRAKOBDH (On-board data handling) merupakan salah satu subsistem satelit yang berfungsi menerima, mengolah, mengambil keputusan dan mengeksekusi perintah dari dan ke satelit. OBDH dibangun berdasarkan dua buah sistem yaitu sistem perangkat keras dan perangkat lunak yang terintegrasi (sistem firmware). Dari sisi perangkat keras, OBDH menggunakan prosesor dengan arsitektur 32bit RISC, 128/256 Kbyte memori internal, dan sistem firmware yang dibangun menggunakan pemrograman primitif. Pemrograman ini menggunakan arsitektur program super loop dan interrupt untuk mengelola sistem agar dapat berfungsi dengan baik. Permasalahan terjadi ketika terjadi kesalahan pada salah satu fungsi pada rutin interrupt sehingga mengakibatkan kegagalan interpretasi perintah atau data dari sensor satelit. Paper ini menjelaskan mengenai implementasi metode penambalan kesalahan pada sistem firmware OBDH satelit LAPAN-A3/IPB yang bertujuan untuk menjaga agar sistem tetap bekerja dengan baik. Verifikasi awal melalui pengujian telah berhasil dilakukan mengunakan engineering model OBDH dan modul hardware in the loop simulators (HWIL). Berdasarkan hasil pengujian, implementasi pada satelit juga telah sukses dilakukan.
PENENTUAN POTENSIAL SEL TEORITIS PROSES ELEKTROLISIS NATRIUM KLORIDA MENJADI NATRIUM PERKLORAT Bayu Prianto
Jurnal Teknologi Dirgantara Vol 6, No.1 Juni (2008)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

Natrium klorida (NaCl) dapat dioksidasi menjadi natrium perklorat (NaClO4) dengan menggunakan metode elektrokimia. Penelitian ini bertujuan untuk menentukan potensial sel teoritis proses elektrolisis NaCl hingga menjadi NaClO4. Proses elektrolis dibagi dalam empat (4) tahapan reaksi pembentukan, yaitu pembentukan : 1) natrium hipoklorit (NaClO), 2) natrium klorit (NaClO2), 3) natrium klorat (NaClO3) dan 4) natrium perklorat (NaClO4). Potensial sel teoritis dipelajari dengan menggunakan metode komputasi dengan perhitungan mekanika kuantum. Dalam penelitian ini digunakan himpunan dasar B3LYP/6-31++G(3df,3pd) dan B3LYP/6-311+G(2d,p) untuk mencari nilai potensial sel teoritis yang mendekati nilai sebenarnya. Hasil penelitian ini menunjukkan bahwa himpunan dasar B3LYP/6-31++G(3df,3pd) lebih akurat untuk menentukan potensial reduksi standar reaksi 2Cl Cl2  2e dibandingkan dengan himpunan dasar B3LYP/6-311+G(2d,p), dengan nilai potensial sel teoritis yang diperlukan untuk proses elektrolisis NaCl hingga menjadi NaClO4 adalah 2,362 Volt sampai dengan 2,918 Volt.
ANALISA AERODINAMIKA KENDALI CANARD ROKET RKX 250 Salam Ginting
Jurnal Teknologi Dirgantara Vol 5, No.1 Juni (2007)
Publisher : National Institute of Aeronautics and Space - LAPAN

Show Abstract | Download Original | Original Source | Check in Google Scholar

Abstract

In the framework of guided missile development in LAPAN, Center of Technology has been rocket designed, constructed and then performed a guided missile trial launching in Pameungpeuk in May 2002. However the result was still far from expectation. It has been realized that numerous of factors played a part in the failure of the missile trial launching, which are structure strenght, propulsion, propellant, guidance system and aerodynamic stability. From all the above factors, aerodynamic static stability is the initial requirement which has to be validated before stepping to the next design process. Based on the above situation, it has been carried out a analysis un RKX 250 rocket aerodynamic static stability with canard guidance which configuration is almost similiar with the one that was launched in Pameungpeuk. To find out the rocket's aerodynamic static stability, a research on lift coefficient and drag coefficient must be done first. From the lift coefficient data, a conduction the center pressure of aerodynamics rocket. Method that is used in this research is the ine which was developed by quadrature multhopp which is analytical method (Krasnov N.F.1978). Keywords: Canard, Dinamika stabilitas, Statik stabilitas, Static margin, Pusat tekanan aerodinamika, Mach number.
Back Pages JTD Vol 15 No 2 Desember 2017 Redaksi Jurnal
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.v15.a2915

Abstract

MODELING AND SIMULATION OF PROLATE DUAL-SPIN SATELLITE DYNAMICS IN AN INCLINED ELLIPTICAL ORBIT : CASE STUDY OF PALAPA B2R SATELLITE - J.Muliadi; Said D.Jenie; A Budiyono
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.a812

Abstract

In response to the interest to re-use PAlapa B2R satellite nearing its End of Life (EOL) time, an idea to incline the satellite orbit in order to cover a new region has emerged in the recent years. As a prolate dual-spin vehicle, Palapa B2R has to be stabilized against its internal energy dissipation effect. This work is focused on analyzing the dynamics of the reusable satellite in its inclined orbit. The study discusses in particular the stability of the prolate dual-spin satellite in the effect of pertubed field of gravity due to the inclination of its elliptical orbit. Palapa B2R physical data was substituted into the dual-spin's equation of motion. The coefficient of zonal harmonics J2 was induced into the gravity-gradient moment term that affects the satellite attitude. The satellites's motion and attitude were then simulated in the pertubed gravitational field by J2 with the variation of orbit's eccentricity and inclination. The analysis of the satellite dynamics and its stability was conducted for designing control system for the vehicle in its new inclined orbit.
ISOMERISASI POLIMER MELALUI REAKSI SAIN SAYEF UNTUK MENGUBAH KONFIGURASI HTPB (HYDROXYL TERMINATED POLYBUTADIENE) POLYMER ISOMERIZATION BY SAIN SAYEF REACTION TO MODIFY CONFIGURATION OF HTPB (HYDROXYL TERMINATED POLYBUTADIENE) Heru Budi Wibowo
Jurnal Teknologi Dirgantara Vol. 14 No. 2 Desember 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.a2387

Abstract

One of the problems in the synthesis of Hydroxyl Terminated Polybutadiene for propellant binders is the level of vinyl is high (up to 30%), while the desired product is 20%. Vinyl bond can be reduced if the chain can be broken with the addition of a hydroxyl group. The research objective is to reduce the amount of vinyl structure in HTPB with the addition of double bonds in the vinyl by applying Sayef Sain reaction. HTPB is reacted with concentrated hydrogen peroxide with the Sain Sayef catalyst in the 1 liter autoclave reactor with ethanol for 1-3 hours at 100° C. After being purified by extraction in hot water and drying, it is analyzed by an infrared spectrometer. The result shows that there is a change in the concentrations of vinyl within the polymers produced by observing the absorption of vinyl groups at a wavelength of 690cm-1. Optimal results obtained with vinyl content of 20% with a temperature of 100° C for 90 minutes. In general, the quality of HTPB can be increased by reducing the levels of vinyl which allowing the HTPB composition to have a vinyl content reduced to 19%. Abstrak:Salah satu permasalahan dalam sintesis Hydroxyl Terminated Polybutadiene untuk binder propelan adalah masih tingginya kadar vinil (sampai dengan 30%), sedangkan produk yang diinginkan adalah 20%. Ikatan vinil dapat direduksi jika dapat dipecah rantainya dengan adisi gugus hidroksil. Tujuan penelitian adalah mereduksi jumlah struktur vinil dalam HTPB dengan adisi ikatan rangkap dalam vinil dengan menerapkan reaksi Sain Sayef. HTPB direaksikan dengan hydrogen peroksida pekat dengan katalis Sain Sayef dalam reaktor autoklaf 1 liter dengan pelarut etanol selama 1-3 jam pada suhu 100 °C. Setelah dimurnikan dengan ekstraksi dalam air panas dan pengeringan dari air, dianalisis dengan spectrometer infra merah. Hasil pengujian menunjukkan bahwa terjadi perubahan konsentrasi kandungan vinil dalam polimer yang dihasilkan dengan pengamatan serapan gugus vinil pada panjang gelombang 690 cm-1. Hasil optimal diperoleh dengan kadar vinil 20% dengan suhu 100 °C selama 90 menit. Secara umum, kualitas HTPB dapat meningkat dengan mengurangi kadar vinil sehingga komposisi HTPB memiliki kadar vinil turun menjadi 19%.

Page 4 of 34 | Total Record : 333

 2   3   4   5   6 

Filter by Year

2003 2022


Reset
Filter By Issues
All Issue Vol 20, No 2 (2022): Jurnal Teknologi Dirgantara Vol 20, No 1 (2022) Vol 19, No 2 (2021) Vol 19, No 1 (2021) Vol. 18 No.2 Desember 2020 Vol. 18 No.1 Juni 2020 Vol. 17 No.2 Desember 2019 Vol. 17 No. 1 Juni 2019 Vol. 16 No. 2 Desember 2018 Vol. 16 No. 1 Juni 2018 Vol. 15 No. 2 Desember 2017 Vol. 15 No. 1 Juni 2017 Vol. 14 No. 2 Desember 2016 Vol. 14 No. 1 Juni 2016 Vol. 13 No. 2 Desember 2015 Vol.13 No. 1 Juni 2015 Vol. 12 No. 2 Desember 2014 Vol. 12 No. 1 Juni 2014 Vol. 11 No.2 Desember 2013 Vol.11 No.1 Juni 2013 Vol.10 No.2 Desember 2012 Vol 10 No.1 Juni 2012 Vol 9, No. 2 Desember (2011) Vol 9, No. 1 Juni (2011) Vol 8, No.2 Desember (2010) Vol. 8 No.1 Juni 2010 Vol 7, No.2 Desember (2009) Vol 7, No.1 Juni (2009) Vol 6, No.2 Desember (2008) Vol 6, No.1 Juni (2008) Vol 5, No.2 Desember (2007) Vol 5, No.1 Juni (2007) Vol 4, No.2 Desember (2006) Vol 4, No.1 Juni (2006) Vol 3, No.2 Desember (2005) Vol 2, No.2 Desember (2004) Vol 2, No.1 Juni (2004) Vol 1, No.2 Desember(2003) Vol 1, No.1 Juni(2003) More Issue