  In this paper we consider the fuel-optimal rendezvous between a satellite and
a spacecraft in a central force field with a drag force that is linear in the
velocity. In this general setting we linearize the equations of motion of the
spacecraft and show that they can be reduced effectively, in the case of a
linear drag, to one second order linear differential equation. We then
specialize to the case of inverse square laws. Under certain simplifying
assumptions a state-transition matrix can be found in terms of integrals. The
work can then be placed in the context of various control models that have been
developed in previouswork. PAPER WAS WITHDRAWN BY AUTHORS. IT will apprear in
AIAA J. Guidance and Control.
