Anti-Tank Guided Missile Performance Enhancement Part-2: Robust Controller Design

Document Type : Original Article

Authors

1 Prof. In Electronics and Electrical Communication Department, MSA University, Cairo, Egypt.

2 Graduate Student in Guidance and Radar Department, MTC, Cairo, Egypt.

3 Asc. 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.

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