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Andri Agus Rahman
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INDONESIA
Indonesian Journal of Aerospace
Published by Badan Riset dan Inovasi Nasional
ISSN : -     EISSN : 30320895     DOI : https://doi.org/10.55981/ijoa
Core Subject : Science, Engineering,
Aerospace Engineering Astronomy
Indonesian Journal of Aerospace provides a broad opportunity for the scientific and engineering community to report research results, disseminate knowledge, and exchange ideas in various fields related to aerospace science, technology, and policy. Topics suitable for publication in the IJoA include (but are not limited to) Space science (astrophysics, heliophysics, magnetospheric physics, ionospheric physics, etc.), Aeronautics technology (dynamic, structure, mechanics, avionics, etc.), Space technology (rocket, satellite, payload system, control, etc.), Propulsion and energetic technology (propellant, rocket static-test, thermodynamics of propulsion system, etc.), Aeronautics and space policy, and Application of aerospace science and technology.
Arjuna Subject : Ilmu Bumi dan Planet (semua kategori) - Ruang Angkasa dan Ilmu Planet
Articles 8 Documents
 1 
Search results for , issue "Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara" : 8 Documents clear
IDENTIFIKASI PARAMETER DAN PERANCANGAN SISTEM KENDALI PID UNTUK ANALISIS SIKAP TERBANG UAV [PARAMETER IDENTIFICATION AND DESIGN PID CONTROLLER FOR FLYING ATTITUDE ANALYSIS OF UAV] Purwanto, Eko Budi; Nasution, Syahron Hasbi; Supendi
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Based on the state space yield first principle method knowed that characteristic of UAV is static stable. To get the near real condition doing verification of state space model by using the identification system toolbox of Matlab. The yield show that matrix element of state space is different both of them. Furher step is design the PID control system base on new state space, and for improve the performance system used Kalman filter.
IMPLEMENTASI 3D GAME ENGINE SEBAGAI VISUALISASI SISTEM NAVIGASI 6-DOF PADA ROKET KENDALI LAPAN [3D GAME ENGINE IMPLEMENTATION AS 6-DOF NAVIGATION SYSTEM VISUALIZATION AT GUIDED ROCKET OF LAPAN] Wiryadinata, Romi; Munarto, Ri; Yusuf, Wildan; Kaharjito, Frandi A
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Game engine, which are often used by game developers, has software framework that facilitates their work on important tasks such as graphic design or 3D and 2D graphics rendering. This research uses game engine called 3D state game engine for visualize 6-DOF navigation system. The software is developed for visualize range of motion of the object by reading and processing the streaming data from navigation sensor (accelerometers and rate-gyroscope). The test result show that developed software can visualize the motion of the objects in 3D animation. Software can accept and process the data as text file that is transmited in real-time through serial port. IMU hardware with sofware can use through the calibration process first, and be given a filter, so that the better results can be obtained.
METODE KALIBRASI SENSOR RATE-GYROSCOPE UNTUK IMU ROKET [CALIBRATION METHOD OF RATE-GYROSCOPE SENSOR FOR IMU ROCKET] Wahyudi; Susanto, Adhi; Widada, Wahyu; Hadi, Sasongko Pramono
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

Rate-gyroscope sensor is used in the IMU to measure the rotation angle in three axes. The output of rate-gyroscope sensor is a voltage which is the angular rate, so to obtain the angle used once an integral process. The integral result of rate-gyroscope sensor depend on sampling time or the cycle time of program to get the datum, so the integral calculation depends on the processor speed of microcontroller (computer). Using of the different sampling time will affect the integral result or in other words we can say that for the same program, if we apply it to a different microcontroller, we will obtain the different calculation. This paper presents the calibration method for determining the calibration factor on the rate-gyroscope sensor, so we will get the actual angle value. The rate-gyroscope sensors on different axes have different characteristics, so each sensor needs to be calibrated. In the experiment results, the calibration factors in three axes are different in both for the clockwise rotation and counterclockwise rotation.
METODE DOPPLER RADIO UNTUK MENGUKUR KECEPATAN ROKET RX200 [RADIO DOPPLER METHOD FOR MEASURING VELOCITY OF ROCKET RX200] Widada, Wahyu
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

This paper discusses the methods and design of radio Doppler to measure the speed of the rocket type RX200. Doppler system consists of a radio transponder to emit a continuous radio signal from the rocket and the radio base station to measure the change in frequency of the radio signal. A change in the frequency of the radio signal caused by the speed of the rocket is used to measure the speed and position of the rocket. The design of radio frequency is 880 MHz transponder adapted to the design speed of the rocket RX200. This method is relatively easy to implement compared with the radar transponder system that has been developed. A simulation of Doppler frequency is performed using the radar data transponder rocket launch experiment RX200 and recomendation of bandwith radio receiver should be 4000 Hz. The combination of these two systems will make a more acurate and reliable tracking system.
MODEL KOREKSI GEOMETRI SISTEMATIK DATA IMAGER PUSHBROOM MENGGUNAKAN METODE PROYEKSI KOLINEAR [PUSHBROOM IMAGER DATA SYSTEMATIC GEOMETRIC CORRECTION MODEL USING COLLINEAR PROJECTION METHOD] Hakim, Patria Rachman; Rahman, Abdul; Suhermanto; Rachhim, Elvira
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

LAPAN-A3 satellite, which is planned to be launched on 2014, will carry a 4 channels pushbroom imager. An image pre-processing is needed to assure that there will be no distortion on the output image data, particularly a systematic distortion, whether it is geometric or radiometric. Systematic geometric correction is intended to eliminate geometric distortion which are predictable such as view angle, earth curvature, earth rotation and varrying camera orientation during observation. The colinear projection method is used in order to transform every pixel on the image into earth coordinate points. Systematic geometric correction needs satellite ancillary data such as position and camera orientation from GPS and star sensor. This research simulated dummy data as substitute to distorted image and ancillary data for designing and simulation purpose. The simulation result shows that the systematic geometric correction algorithm is able to correct the distortion occured in image. A corrected image with 1000 meter accuracy can be achieved with 0,1 degree orientation data accuracy while 0,01 degree orientation data accuracy produces an even better 100 meter accuracy corrected image for nadir observation.
PENGARUH NILAI KOEFISIEN AERODINAMIKA DAN PADA KESTABILAN TERBANG GERAK PERIODE PENDEK (SHORT PERIOD) RKX-200 LAPAN [EFFECT OF AERODYNAMICS COEFFICIENT VALUE AND TO THE STABILITY OF THE FLY MOTION SHORT PERIOD RKX-200 LAPAN] GS, Endang Mugia
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The rocket flew of short period modes of motion, can be used as a way to measure the stability of the rocket flying. By performing simulation using software Missile DATCOM obtained aerodynamic coefficient and , each of which affects the value of the natural frequency and damping motion short period. RKX-200 Lapan rocket is a quite stable rocket. And the magnitude of the aerodynamic coefficient : -0,12 to -.0,02 and value of : -2,4 to -1,2, with each value remains negative at cruising speed prediction of 0,1 M s.d 2,0 M. It’s good enough to be the guided missile with value 0,18  SM  0,46.
EVALUASI KINERJA SAMBUNGAN PROPELAN PADA MOTOR ROKET RX 550 [EVALUATION OF THE PROPELLANT JOINT PERFORMANCE IN ROCKET MOTOR RX 550] Sutrisno
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Abstract

The propellant joints quality of RX 550 rocket motor using segmented HTPB propellant was become a debatable. In static test this rocket motor exploded and the nozzle was broken out at seven second after ignition. To evaluate these propellant joints the propellant installation in rocket motor was discused. The propellant joint strength was tested using Tensilon UTM III-100 test equipment. The rocket motor tube at the propellant joint position were marked and investigated before and after static test. The datas such as thrust and chamber pressure versus time were analyzed for finding the posibility of joints defect. Based on analysis it is found that the propellant joint can work well. The RX 550 rocket motor failure in static test didn’t caused by propellant joints.
SIMULASI CFD PADA DIFFUSER AUGMENTED WIND TURBINE (DAWT) : EFEK BENTUK INLET DAN PANJANG DIFUSER TERHADAP DISTRIBUSI KECEPATAN ANGIN DI EXIT DIFUSER Atmadi, Sulistyo; Fitroh, Ahmad Jamaludin
Indonesian Journal of Aerospace Vol. 10 No. 2 Desember (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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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.

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