• Trade-off cost impacts of high packaging density in launch vehicles and space fabrication versus a policy to assemble low density ground fabricated components in orbit. Following these near term studies. Ref. All proposes a three phase development program. The pertinent launch vehicle details of this program are outlined as follows: Phase I Space Shuttle 15 MW Demonstration LEO 1985 Phase II Shuttle Derivative 1 GW Pilot Plant GEO 1990 Phase III HLLV 5 GW Operational Plant GEO 1995 To meet this schedule, the HLLV would be developed from 1985 to 1992, thus becoming operational in 1992. For solar-thermal approaches, Ref. E9 also proposes a three phase development program, which can be summarized as follows: 1982-1984 Low orbit Shuttle based experiments 1985 GEO prototype, if needed, in operation 1991 Initial operational capability This program would require the first HLLV in 1988, with a total of 8 HLLVs required by 1996. Shuttles would be used for personnel transport. Reference E7, which deals with the solar-thermal concept, briefly describes the HLLV as a fully reusable "LEO Freighter" with a 500,000 pound (225,000 kilogram) payload capacity. All ground handling would be by waterborne towing and a new lake at the Kennedy Launch Complex would serve as a landing basin for this vehicle. 6 Reference E7 states that the vehicle would weigh about 22 x 10 6 6 pounds (10 x 10 kg) at lift off, with an empty weight of about 2 x 10 0 pounds (1 x 10 kg). It would use LH^/LC^ as the primary propellant and RP^/LO^ propellant during the first 110 seconds for boost assist and for deceleration for a "soft landing." The technology and materials for this vehicle are said to be similar to those developed on the Saturn program, but with the added features of greater safety, a water-cooled reusable heat shield, and fully sealed engine compartments. The primary flight mode would be a "once-around" orbit with the payload being deployed on the backside of the orbit.
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