Anti-Tank Guided Missile Performance Enhancement Part-2: Robust Controller Design | ||||
The International Conference on Electrical Engineering | ||||
Article 59, Volume 5, 5th International Conference on Electrical Engineering ICEENG 2006, May 2006, Page 1-13 PDF (211.93 K) | ||||
Document Type: Original Article | ||||
DOI: 10.21608/iceeng.2006.33655 | ||||
View on SCiNiTO | ||||
Authors | ||||
G. A. El-Sheikh1; M. A. Abd-Altief2; M. Y. Dogheish3 | ||||
1Prof. In Electronics and Electrical Communication Department, MSA University, Cairo, Egypt. | ||||
2Graduate Student in Guidance and Radar Department, MTC, Cairo, Egypt. | ||||
3Asc. Prof. In Electronics and Electrical Communication Department, MUST, 6th October, Cairo, Egypt. | ||||
Abstract | ||||
Abstract The performance of antitank guided missile systems is measured through the minimum missdistance and its capability to overcome target maneuver and different sources of errors including disturbances and noises. Toward these performance constraints, the guidance and control is considered, which is one of the most interesting and challenging problem areas for antitank missile. Therefore, this paper considers an antitank guided missile system belonging to the first generation for the design and analysis. The design and analysis necessitates somehow accurate model (objective of Part-1 of the paper) for the system and a robust control design philosophy (objective of Part-2 of the paper). Transfer functions representing the missile-control system dynamics in pitch and yaw planes are identified via hardware in the loop (HWIL) simulation and considered for investigation and validation against previous work and reference flight data. These transfer functions are obtained and justified in Part-1 of the paper and consequently this part is devoted to design a robust controller and implements it within the 6DOF simulation. The jetvator control loop for both pitch and yaw channels of the intended guided missile system with compensation network are designed using ∞ H and investigated such that the system is stabilized and the performance requirements are satisfied with disturbance rejection and measurement noise attenuation. To stay on the robustness of these controllers and their ability to withstand against disturbances, the measurements are corrupted with noise and the system performance is investigated. The obtained results showed superior features of ∞ H in stabilizing the system with only one controller allover the flight envelope and withstand some of the uncertainty sources. | ||||
Keywords | ||||
Guidance and Control; Hardware-in-Loop Simulation; system identification; Robust Control | ||||
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