The specific elements used to characterize an SSP architecture in this study are identified and defined in Section 5 where the Integrated Architecure Assessment Model (LAAM) is described. Apart from financial scenario elements that the IAAM model employs to carry out its economic evaluation function, the key architecural elements that discriminate each proposed system are: • SSP System Manufacturing • Ground Launch Infrastructure • ETO Transportation System • In-Space Transportation • In-Space Infrastructure • SSP Space Segment • SSP Space Segment Relay • SSP Ground Segment • Commercial Power Utilities Interface • Markets The concept descriptions to follow employ a standard textual format in attempting to capture our current understanding of each of these elements. System drawings and architectural diagrams are also provided to further illustrate each concept. Because it has been used as the basis for comparison throughout this “fresh look” study, the concept descriptions begin with the 1979 Reference system. 3.2. 1979 Reference Concept The 1979 SPS Reference System (SRS-’79) from the DoE/NASA space solar power study involves the extensive use of in-space assembly and construction by astronaut crews in low Earth orbit to build very large, conventional structural concept platforms that were then transported to geostationary Earth orbit (GEO). In particular, the system architectural concept entails establishing a family of sixty platforms in GEO, each producing a net 5 GW for a single, dedicated receiver location on the ground. Figure 3-2 provides a top-level illustration of the SRS-’79 system concept, including various supporting infrastructure elements. The concept requires the development of significant dedicated transportation and in-space infrastructure elements. SRS-’79: Development & Manufacturing. The SRS-’79 concept entails significant ‘unique’ developments as well as several system components winch — once developed — could be manufactured at a moderate price. System-level manufacturing reaches a moderate level of ‘mass construction’ after the first several systems are deployed, but not mass production. Earth-to-Orbit Transportation. Extensive concept-imique ETO transportation systems are required, with payloads of approximately 100,000 MT. In particular, a fully-reusable, two-stage-to-orbit (TSTO) heavy lift launch vehicle (HLLV) is included in the SRS-’79 architecture. Extensive new, concept-unique ground launch infrastructure is required as a result of the need for both heavy lift and highly reusable, very low cost ETO transportation. In-Space Transportation. A unique, extremely affordable LEO-to-GEO in-space transportation is required following system deployment, which takes place in LEO. This system is projected in the reference concept to be a kilometer-sized, solar electric propulsion system (SEPS) orbital transfer vehicle.
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