چكيده لاتين :
In this paper, analytical solution of the generalized collision COUTse (Gee) is
presented considerino appTOximate models fOT draq and thrust in the presence of
gmvity. The Geeis near optimal fOT a considerable flight time toward the end.
Therejore, guidance laws based on Gee only need modification for the first stage
of flight. The proposed guidance law is a modification of midcourse siratcqies
based on the GGe and its implementation issues. A Tecursive relation [or
estimation of time-to-go for the Geeis presented in order to reduce the onboard
computational burden. Two other recursive relations for time-to-go are obtained
fOT optimal guidance laws. The relations can be used for both mulcourse
and terminal applications. For an aeTOdynamically controlled interceptor, the
guidance law produces the commanded acceleration in the direction normal to
its velocity vector orי appToximately normal to its body axis. Simulation results
show that the presented stmtegy is superior to the midcourse guidance laws
based on Geefor a qreater final velocity.
