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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 8 Documents
 1 
Search results for , issue "Vol 9, No. 1 Juni (2011)" : 8 Documents clear
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

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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
ALGORITMA DETEKSI SUDUT AZIMUT DAN ELEVASI ROKET MENGGUNAKAN SEMBILAN ANTENA ARRAY YAGI-UDA Satria Gunawan Zain; Adhi Susanto; Thomas Sri Widodo; Wahyu Widada
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 Radiation pattern of Yagi-Uda antenna is elliptical. This pattern can be used as a detector for the direction of the source of a radio emission. A total of nine Yagi-Uda antennas fitted with a 3x3 configuration. With this configuration, the measurement range for azimuth and elevation angles can reach 80º. The simulation was performed by using an antenna radiation pattern data. The number of antennas used for this simulation is nine. Then the data is merged into a 3x3 antenna configuration data. Based on data from nine antenna radiation patterns, the algorithm for the estimation of azimuth and elevation angles can be applied. Simulation results show that the measurement error of the signal without noise is close to zero. The algorithm used in this simulation can be applied to noise below 25%. Key word:Angle Estimation, Noise effects, Yagi-Uda Antennas, Rocket movement estimation
ANALISIS LOSSES PIPA LURUS BERDIAMETER 40 cm PADA TEROWONGAN ANGIN LAPAN Ahmad Jamaludin Fitroh
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 One of LAPAN’s programs is design and build the ramjet open tested wind tunnel. The lenght of pipe connecting between wind tunnel and storage tank was designed long enough so it was estimated there is big losses along the pipe. The object of this research is to calculation that losses, specially for the straight part only. The magnitude of the losses was gotten from simulation using software based on CFD theory. This research used two methods, i.e. based on pressure method and based on mass flow rate method. The simulation’s result using based on mass flow rate method gave the higher losses for the straight pipe so that result was chosen as the final result. That result was processed become the losses as a function of mass flow rate. The higher mass flow rate will produce the bigger losses. At mass flow rate of 60 kg/s, the losses is 0.135 %/m and at 100 kg/s the losses is 0.299 %/m. The relation between both parameter is close to linier curve. Key word:Pipe, losses, CFD, wind tunnel
DESAIN NOSEL ROKET CAIR RCX250 MENGGUNAKAN METODE PARABOLIK DENGAN MODIFIKASI SUDUT EKSPANSI Eko Priamadi; Arif Nur Hakim; Romie O. Bura
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 The present research is conducted to design the optimum nozzles for RCX250 engine, that is designed to produce maximum thrust of 250 kgf with combination of LOX and Kerosene as its propellant. The new nozzles were determined to be parabolic nozzle, with conical nozzle as its comparison. The parabolic nozzle was designed using Thrust Optimized Parabolic (TOP) method invented by G.V.R.Rao. TOP nozzle design method is performed by approximating a Thrust Optimized Contoured (TOC) Nozzle using parabolic equation. The method would result more efficient nozzle than conical or ideal bell nozzle. Further, the parabolic nozzle were modified in its initial and exit angle to create uniform velocities distribution at nozzle exit. A Computational Fluid Dynamics Method (CFD) is used to simulate the nozzle designs. The simulation was carried out in axis-symmetric condition using commercial CFD software. The simulation results show that MOD 1 nozzle, with initial angle (θN) 26 deg and exit angle (θe) 12 deg, gives maximum thrust, which is 4.67 % higher than reference conical nozzle. Key words:Liquid rocket, Parabolic nozzle, Thrust, CFD
ESTIMASI BIAYA DAUR HIDUP DAN OPTIMISASI HARGA PESAWAT TERBANG Rais Zain; Odi Ahyarsi
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 Since the conceptual design phase, the estimate of airplane life cycle cost (LCC) is carried out to support a decision making process. The LCC consist of research, development, testing, and evaluation cost, where an airplane estimated price (AEP) is a part of this calculation. Furthermore, AEP is employed as a non linear objective funtion for developing a constrained optimization algorthm. Rosen’s gradient projection is applyed in the development of computer program named Cost Analysis implementing object oriented approach on Microsoft Visual C++ 6.0. In order to verify the application, some data of Ourania jet airplane were utilized for carrying out a case study. The result of Cost Analysis shows that the estimated LCC are similar to the reference. Also, the optimization problems can be solved by Rosen’s algorithm less than ten iterations. Keywords:Conceptual aircraft design, Life cycle cost, Object oriented approach, Visual C++
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
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
SIMULASI GERAK DAN ANALISIS KESTABILAN KOPLING INERSIA WAHANA DIRGANTARA DENGAN BENTUK BADAN RAMPING Hari Muhammad; Hilman Samputra; Yazdi I. Jenie; Javensius Sembiring
Jurnal Teknologi Dirgantara Vol 9, No. 1 Juni (2011)
Publisher : National Institute of Aeronautics and Space - LAPAN

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Abstract

 Inertia coupling is a motion phenomenon of a high-speed airplane having slender body and low aspect ratio. This inertia coupling happens when the aircraft performs a roll manoeuvre motion with a high roll rate. This paper will discuss the derivation of inertia coupling equations of motion, modelling equations of motion in the Matlab/Simulink software, simulating the dynamics motion, and analyzing the stability of the inertia coupling. Numerical simulation and stability analysis of the inertia coupling for a fighter aircraft will be presented in this paper. Keywords:Inertia coupling, Stability analysis, Flight simulation, Slender body

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