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PURWANTO, EKO BUDI
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Aerospace Engineering Astronomy

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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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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.
PEMODELAN SISTEM DAN ANALISIS KESTABILAN DINAMIK PESAWAT UAV (MODELING SYSTEM AND DYNAMIC STABILITY ANALYSIS OF UAV) Purwanto, Eko Budi
Indonesian Journal of Aerospace Vol. 10 No. 1 Juni (2012): Jurnal Teknologi Dirgantara
Publisher : BRIN Publishing

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Mission of Unmanned Aerial Vehicle (UAV) “Elang Avionik†is surveillance and aerial photographs. Therefore the flight of UAV must be stable and controlable, and first step activity is dynamic modelling and stability analisys. The problems of UAV system is disturbance, noise of sensor, MIMO and uncertainty dynamic model. For good result using the multivariable robust control, with some step research that is: (1)modeling and stability analysis, (2) design and implementation of PID control system, (3) flight dynamic parameter identification, (4) design and implementation of hardware in the loop simulation, (5) design and implementation of multivariable robust control, (6) test and evaluation of system. Simulation result show that the eigen value in longitudinal is: phugoid mode = –0,061293±0,40526i and non-oscillation mode = –6,1121±4,9253. In lateral directional is:dutch roll mode = –0,91089±5,7994i, spiral mode= –0,036563, and roll subsidence mode = –12,7181. Location of poles system on the left of imaginary axis, the means that the character of system is dynamic stable. But settling time to steady state condition is very long and improved by control system design.Key word: State space, Longitudinal, Lateral, Stable static, Stable dynamic
SISTEM KONTROL SUN SEEKER SUATU MODEL UNTUK MENGENDALIKAN PERILAKU WAHANA ANTARIKSA Purwanto, Eko Budi
Indonesian Journal of Aerospace Vol. 5 No. 1 (2007): Vol 5, No.1 Juni (2007)
Publisher : BRIN Publishing

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Sun seeker control system doing by monitoring the sun as main reference. The result of monitoring the sun position used for the line correction of space vehicle. In these paper used simulation method for gated parameter value control system. To know the influence of sun seeker control system, simulation was doing with and without lead compensator. The result of simulation show that without sun seeker control system the time settling is ts = 0.35 second and maximum overshoot Mp = 44,4 percent. These results not reasonable for controling of plan with high velocity like rocket and satellite. Later simulation with phase lead sun seeker control system, give settling time ts = 0,12 second and maximum overshoot Mp 5 percent. From the simulation data that sun seeker control system can used for space vehicle control and agree with steady state error specification.Keywords: Sun seeker control system, FFase lead, Waktu penetapan, lewatan maksimum, kondisi tunak
Co-Authors Nasution, Syahron Hasbi Supendi