REPUBLIC OF SERBIA

MINISTRY OF DEFENCE

www.mod.gov.rs

MINISTRY OF DEFENCE

Material Resources Sector

Defensive Technologies Department

Military Technical Institute

www.vti.mod.gov.rs

SLIDING MODE GUIDANCE OF HOMING MISSILEs VS. TRUE AND AUGMENTED PROPORTIONAL NAVIGATION

Miloš Pavić

Vojnotehnički institut, Beograd, cnn@beotel.rs.rs

Bojan Pavković

Vojnotehnički institut, Beograd, bjnpav@gmail.com

Danilo Ćuk

Faculty of Mechanical Engineering, Belgrade, Serbia, cukd@eunet.rs

Abstract: High performance criteria are required from homing missiles against maneuvering targets. In the practice, commonly used guidance laws are the True Proportional Navigation and the Augmented Proportional Navigation (second one if the target maneuver can be measured or estimated). Better performances can be achieved using some of the Optimal Guidance Laws, but they require additional time-to-go measurement or estimation. In this paper, a Sliding Mode Guidance based control law is presented as an adaptive control law for homing missiles, without the measurements of the time-to-go or missile maneuver (its normal acceleration). Sliding mode guidance control law parameters are tuned in parametric plane considering two criteria - final miss distance and total energy consumption during guidance. Analysis is performed for a non-ideal missile model, represented with an assumed time constant. Simulation results include comparison with the True Proportional Navigation and the Augmented Proportional Navigation for the same engagement scenarios with the varying instant of the target maneuver and the initial Heading Error.

Key words: sliding mode control, proportional navigation, homing, and missile.