Other candidates were two-stage ballistic entry vehicles of four types and a final candidate HLLV was devised to achieve the capability of providing alternative launch service for cargo or a personnel carrying vehicle derived from the Space Shuttle Orbiter. There has not been any attempt as yet to define the optimum size size of the launch vehicle nor at this moment can significant differences be detected between their potential cost effectiveness. As the configuration definition evolves and additional cost data becomes available, the candidate vehicles may be narrowed to a baseline configuration. Reduction to a single baseline vehicle is not considered appropriate until the cost data is available and requirements more thoroughly understood consequent to the satellite design activity. 3.2 Personnel and High Priority Cargo Launch Vehicle (PLV) The assumption is made that man rating of the HLLV will constitute an incremental cost upon its development and operation. For this reason and for the operational flexibility provided, an entirely separate launch vehicle is presumed required to serve the needs of the satellite power station program. This vehicle will be utilized to transport all personnel to low Earth orbit and can in addition fulfill high priority delivery functions of a modest scale. Although a new vehicle such as a single-stage-to-orbit (SSTO) may be developed to fulfill this need, the justification for embarking upon the development program of a "clean sheet" design is not immediately evident. Consequently, the approach taken in this study is to modify the current Shuttle vehicle to fulfill these needs. Studies have indicated that the baseline Shuttle system can be improved in both payload capability and operating cost by replacement of the solid rocket booster with a new booster utilizing liquid oxygen and kerosene propellants. Such a booster can be provided using the F-l engines from the Saturn V first stage. If available for heavy lift vehicle use, a new, more efficient, hydrocarbon/oxygen engine can be advantageously employed. The payload capability assumed for sizing this new booster is 100,000 pounds to the mission one requirements of the current baseline Shuttle. A more important parameter than payload weight for this vehicles application to satellite power program needs may be its ability to carry a number of personnel on each flight. Brief studies have been performed which indicate that, given the maturity of operation to be provided by the baseline shuttle operation, modifications to the Shuttle Orbiter may be accomplished to enable transportation to low Earth orbit of 50 to 80 persons per flight. These modifications can be incorporated in orbiter vehicles taken from the operational fleet should that prove to be financially advantageous. 3.3 Cargo Orbital Transfer Vehicle (COTV) The characteristics of the cargo OTV will be largely shaped by the choice of satellite power station construction location. If the low Earth orbit may be employed for assembly of power producing payload elements, their power output may be utilized for electric thrusters to
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