Terminal Maneuvers for Satellite Ascent Rendezvous

Abstract

The terminal phase of ascent rendezvous is analyzed to determine the opt imum aiming point for the ascent trajectory of a maneuverable satellite and an opt imum steering program for guiding the satellite to rendezvous with its target once the target has been acquired with an on-board active sensor. For perfect initial conditions, the ideal rendezvous path under constant thrusting is developed with the constraint tha t the thrust vector always be coincident with the velocity vector. An aiming point (for a case without errors) where the rendezvous maneuver should be initiated is described for the ascent ellipse. An opt imum steering control program for the control of the thrust vector relative to the line of sight vector is developed for guiding the interceptor to rendezvous even when the ideal initial conditions of position and relative velocity vector orientation are not achieved at the end of the interceptor's transfer trajector.