SSME's. Its payload can be a modified Orbiter (which does not require a main propulsion system) with a 45-ton payload or a personnel carrier module carried internally in the payload bay or a much larger payload in an aerodynamic shroud. The external hydrogen tank is separated and reentered in a remote ocean region as is the Space Shuttle external tank. The configuration and characteristics are shown in figure VI-1. The two-stage winged candidate is a 450-metric ton payload launch vehicle that accepts a potentially higher unit cost than water- recovered vehicles in order to acquire the operational advantages of airplane-like recovery. Several configurations, burn sequences, and engines were investigated and are described in Volume II„ The characteristics and configuration of a selected design using 20 LOX/propane (CgHg) engines are shown on figure VI-2, along with the characteristics Figure VI-1.- Modified single-stage-to-orbit launch vehicle.
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