Robust CLOS Guidance and Control: Part-3: HIL Systems Simulation

Oda, A. N.; El-Sheikh, G. A.; El-Halwagy, Y. Z.; Al-Ashry, M.; Abd-Altief, M. A.

doi:10.21608/asat.2011.23225

Robust CLOS Guidance and Control: Part-3: HIL Systems Simulation

Document Type : Original Article

Authors

¹ Egyptian Armed Forces, Egypt.

² Professor.

10.21608/asat.2011.23225

Abstract

The great developments in applied mathematics and computational capabilities facilitate the design and implementation of robust control. In addition, the huge developments in nanotechnology and its availability in civilian level with less cost, size and weight attract many of the researchers allover the world towards embedded systems especially the embedded flight control. Among the real applications are the guided missiles especially the antitank guided missile systems which are commanded to the line of sight (CLOS) against ground and short range targets. The present work is concerned with improving the performance of an antitank guided missile system belonging to the first generation via robust synthesis of autopilot and guidance systems. The design and analysis necessitates somehow accurate model with different uncertainties (objective of Part-1 of the paper) for the system, a robust autopilot design (objective of Part-2 of the paper) and implementation via hardware in the loop (HIL) simulation (objective of Part-3 of the paper). This part of the paper is devoted to conduct the simulation with Jetvator hardware (pitch and yaw) in the loop and the robust autopilot obtained in the previous part of this paper. It starts by identifying the Jetvator dynamics on-line and within the closed loop from which the transfer function is used in justifying the designed autopilot via time responses and the 6DOF simulation. Then, the Jetvator hardware is implemented within the 6DOF simulation via interfacing cards using the designed robust autopilot in presence of the prescribed sources of uncertainty. The results show the model accuracy via using the HIL simulation with systemidentification which has clear effect upon enhancing the system performance and gives the green light for the next step of implementing the designed robust autopilot with the HIL. The obtained results are very promising clarifying the autopilot capability to stabilize the system (in pitch and yaw) with the HIL and in presence of disturbance and measurement noise.

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