Abstract:
An explicit, closed form formula of discrete advanced guidance law for a linear, time-invariant, high-order and acceleration-constrained missile and a linear, time-invari...Show MoreMetadata
First Page of the Article

Abstract:
An explicit, closed form formula of discrete advanced guidance law for a linear, time-invariant, high-order and acceleration-constrained missile and a linear, time-invariant arbitrary-order, maneuvering target is derived. The formula is given in terms of the missile's transfer function and acceleration constraint, the shaping filter of the target and responses to initial conditions. Optimal full state feedback guidance law is synthesized and compared to a first order approximation for minimum and non-minimum phase missile. Simulation of a third order missile model shows the relative gain from using the full state guidance law for several values of the missile time response and acceleration constraint.
Date of Conference: 25-27 May 1993
Date Added to IEEE Xplore: 06 August 2002
First Page of the Article
