An apparatus and method for launching a spacecraft (200) including a payload (202) and a delivery stage (204) having a rocket engine (37) powered by fluid bipropellant (114) from the earth into a high energy orbit and for recovering the delivery stage (204). By reducing the delivery stage mass, it becomes feasible and cost effective to recover the delivery stage (204) for reuse. Delivery stage mass is reduced by several techniques including transporting the spacecraft (200) and the fluid bipropellant (114) to a parking orbit with the fluid bipropellant in tanks (20-26) external to the spacecraft (200); transferring the fluid bipropellant (114) to light weight tanks (30-36) integral to the spacecraft (200); controlling the relative flow rates of the fluid bipropellant constituents to the rocket engine (31) during firing of the rocket engine (37) to ensure complete use of both bipropellant constituents; and controlling ascent and descent maneuvers from remote tracking stations. A space shuttle (42) can be used to transport the spacecraft (200) and fluid bipropellant (114) in its cargo bay (40) to the parking orbit and recover the delivery stage (204) at the end of a mission. The invention is particularly useful for delivery of payloads to geosynchronous orbits.