Abstract

Modified guidance law based on a sliding mode controller for a missile guidance system

Highlights

  • A guided missile system performance depends on its G&C algorithms

  • This paper addresses an application of the sliding mode control to design a robust missile command guidance law

  • The success of the proposed method is attributed to the type of new command (u1, u2) generations. These commands are proportionate to the error rate angle between the missile and sliding line eė 2, in addition, the simulation results indicate less chatter about the line-of-sight in modified guidance and control sliding mode controller (MGCSMC) than in the proportional navigation (PN) method, which enables the missile to reach the target without losing more energy

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Summary

Introduction

A guided missile system performance depends on its G&C algorithms. Several important functions were performed by using such algorithms. G&C algorithms contain adjustable design parameters that control their operation and final performance [8, 9]. The sliding mode controller (SMC) law is a substantial case from the large class commonly referred to as the variable structure control. An advantage of these control methods is their robustness to parameter perturbations and bounded external disturbances [13]. This paper addresses an application of the sliding mode control to design a robust missile command guidance law. Modified guidance law based on a sliding mode controller for a missile guidance system

Kinematic equations of missile and target
Sliding mode design
Simulation scenarios
Flowchart and schematic of the MGCSMC
Results and Discussion
Conclusion
Full Text
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