On-line Control Technique for Missile Autopilot
Abo-Elela, M., El-Shabrawy, A., Hassan, I. (2010). On-line Control Technique for Missile Autopilot. EKB Journal Management System, 7(7th International Conference on Electrical Engineering ICEENG 2010), 1-8. doi: 10.21608/iceeng.2010.32994
Magdy Abo-Elela; Ayman El-Shabrawy; Ibrahim Hassan. "On-line Control Technique for Missile Autopilot". EKB Journal Management System, 7, 7th International Conference on Electrical Engineering ICEENG 2010, 2010, 1-8. doi: 10.21608/iceeng.2010.32994
Abo-Elela, M., El-Shabrawy, A., Hassan, I. (2010). 'On-line Control Technique for Missile Autopilot', EKB Journal Management System, 7(7th International Conference on Electrical Engineering ICEENG 2010), pp. 1-8. doi: 10.21608/iceeng.2010.32994
Abo-Elela, M., El-Shabrawy, A., Hassan, I. On-line Control Technique for Missile Autopilot. EKB Journal Management System, 2010; 7(7th International Conference on Electrical Engineering ICEENG 2010): 1-8. doi: 10.21608/iceeng.2010.32994

On-line Control Technique for Missile Autopilot

The International Conference on Electrical Engineering
Article 41, Volume 7, 7th International Conference on Electrical Engineering ICEENG 2010, May 2010, Page 1-8  XML PDF (248.79 K)
Document Type: Original Article
DOI: 10.21608/iceeng.2010.32994
View on SCiNiTO View on SCiNiTO
Authors
Magdy Abo-Elela1; Ayman El-Shabrawy2; Ibrahim Hassan2
1College of Engineering, Cairo University, Cairo, Egypt.
2Egyptian Armed Forces.
Abstract
In this paper a new learning strategy is used for on-line tuning the control system of the ballistic missile. The gradient descent method technique is utilized to derive the on-line tuning laws of the robust controller, so that the robust performance of the system can be yielded. As the result of using this method, the old technique “gain schedule” that normally used in ballistic missile is replaced. The simulation result shows a good settling time, less or no overshoot and higher robustness were achieved. Moreover, the new tuning process is successful in the presence of high noise.
Keywords
PID tuning; Missile control system and Gradient descent
Statistics
Article View: 112
PDF Download: 217