• In LEO, the logistics and OTV engine and propellant depots are in an orbit different from the construction depot so that there are two HLLV launch windows per day. • The HLLV delivers its payload into an 80 x 435 km orbit. The kick or second stage of the HLLV may circularize, rendezvous, and dock the payload with the appropriate depot, or a LEO tug may perform these functions. • The COTV retrieves its payload from a LEO depot and delivers it to GEO. • The shuttle rotates personnel between Earth and a LEO space station. • The POTV rotates personnel between LEO and GEO. 9. 2. 2 LOGISTICS EQUIPMENT AND TRANSPORTATION A transportation analysis has been performed for a 30 year program with either a photovoltaic or thermal SPS assembled in LEO or GEO. The mass of the photovoltaic system assembled in LEO is assumed to be 144. 78 x 106 kg with logistics resupply requirements of 1. 36 x 106 kg/year. The photovoltaic system assembled in GEO is assumed to have a mass of 107.48 x 106 kg with logistics resupply requirements of 1.16 x 106 kg/year. The thermal SPS assembled in LEO is assumed to have a mass of 274.46 x 106 kg, while the GEO assembled version has a mass of 221. 34 x 106 kg. The logistics resupply is 0. 85 x 10G kg/year for both. For each SPS case outlined above, nine transportation cases were analyzed as follows: 1. Gas Core Reactor (GCR) POTV a. GCR COTV b. Single Stage to Orbit (SSTO) HLLV 2. Chemical POTV a. GCR COTV b. SSTO HLLV
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