Shuttle-to-geostationary orbital transfer by mid-level thrust

This paper describes a method for determining the trajectory and the related maneuver requirements (initial conditions, steering angles, and time sequence of events) for transferring a space vehicle, by means of a two-burn mid-level thrust propulsion, from low, inclined, parking orbit to geostationary orbit. The method has been applied to a number of constant thrust and constant acceleration transfers, and the results are displayed in parametric curves showing the trade-offs (efficiency, transfer time) of this approach versus the high thrust Hohmann transfer. The sensitivity of propellant requirement to thrust direction is also investigated.