Paper Info
Title
Terminal Impact Angle Constrained Guidance Laws Using Variable Structure Systems Theory
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.
Year
DOI
Venue
2013
10.1109/TCST.2013.2276476
Control Systems Technology, IEEE Transactions
Keywords
Field
DocType
acceleration control,control system synthesis,impact (mechanical),missile control,nonlinear control systems,variable structure systems,latax,line-of-sight angle,maneuvering targets,missile lateral acceleration,nonlinear engagement dynamics,principal operating mode,sliding mode control,switching logic,switching surface,terminal impact angle constrained guidance laws,variable structure system theory based guidance laws,Guidance,impact angle,missiles,sliding mode control (SMC)
Acceleration control,Systems theory,Nonlinear system,Control theory,Missile,Control engineering,Acceleration,Variable structure control,Law,Mathematics,Sliding mode control
Journal
Volume
Issue
ISSN
21
6
1063-6536
Citations 
PageRank 
References 
5
0.55
6
Authors
2
Name
Order
Citations
PageRank
Sachit Rao1543.55
Debasish Ghose277771.57