Evaluation and enhancing missile performance via real time flight simulation model

Abstract

Simulation is a very important tool of design and development of systems; especially in the field of guidance and control. This paper discusses first, the implementation and evaluation of a real time Six Degree Of Freedom (6DOF) flight simulation model for a Skid-To-Turn (STT) Infra Red (IR) rolling missile with a single plane of control. Second, applying True Proportional Navigation (TPN) instead of Classical Proportional Navigation (CPN) guidance law that is used in guidance system of real missile. As a result of applying TPN guidance law, the autopilot gain in the flight control system is recalculated to enhance missile performance. Simulation results when using TPN guidance law are evaluated and compared with simulation results when using CPN guidance law. The comparison results prove that TPN increases the ability of missile to hit more speed and maneuvering targets.