Terminal Impact Angle Constrained Guidance Laws Using Variable Structure Systems Theory

Rao, Sachit and Ghose, Debasish (2013) Terminal Impact Angle Constrained Guidance Laws Using Variable Structure Systems Theory. In: IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY, 21 (6). pp. 2350-2359.

PDF IEEE_Tra_Con_Sys_Tec_21-6_2350_2013.pdf - Published Version Restricted to Registered users only Download (629kB) | Request a copy

Abstract

In this brief, variable structure systems theory based guidance laws, to intercept maneuvering targets at a desired impact angle, are presented. Choosing the missile's lateral acceleration (latax) to enforce sliding mode, which is the principal operating mode of variable structure systems, on a switching surface defined by the line-of-sight angle leads to a guidance law that allows the achievement of the desired terminal impact angle. As will be shown, this law does not ensure interception for all states of the missile and the target during the engagement. Hence, additional switching surfaces are designed and a switching logic is developed that allows the latax to switch between enforcing sliding mode on one of these surfaces so that the target can be intercepted at the desired impact angle. The guidance laws are designed using nonlinear engagement dynamics for the general case of a maneuvering target.

Item Type:	Journal Article
Publication:	IEEE TRANSACTIONS ON CONTROL SYSTEMS TECHNOLOGY
Publisher:	IEEE-INST ELECTRICAL ELECTRONICS ENGINEERS INC
Additional Information:	copyright for this article belongs to IEEE Xplore
Keywords:	Guidance; impact angle; missiles; sliding mode control (SMC)
Department/Centre:	Division of Mechanical Sciences > Aerospace Engineering(Formerly Aeronautical Engineering)
Date Deposited:	22 Nov 2013 11:27
Last Modified:	22 Nov 2013 11:27
URI:	http://eprints.iisc.ac.in/id/eprint/47781

Actions (login required)

View Item