A Modified Midcourse Guidance Law Based on Generalized Collision Course

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 or 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.