Figure VI-9.- Crew rotation passenger module. The common-stage concept consists of two nearly identical stages used in series to provide the required mission delta velocity. The first of these stages is used to provide approximately 85 percent of the delta velocity required for acquiring the elliptical geosynchronous transfer orbit on a crew rotation flight. The second stage provides the remainder of the transfer delta velocity as well as that required for circularization at the destination orbit and both of the return maneuvers. Following separation from stage 2, stage 1 is retrograded into the Earthcircular departure orbit. Splitting the delta velocity in the above manner results in the stages having identical propellant capacities. Subsystems design approaches are also common between the stages, including the size of the main engine. A representative POTV^ configuration and characteristics are shown on figure VI-10, together with the crew module. The dimensions of the stages are Shuttle compatible but due to their propellant requirements will require on-orbit fueling/refueling. A 75-man crew rotation module plus over 20 metric tons of priority cargo can be carried to GEO in the operating mode wherein stage 2 is refueled at GEO.
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