The results of the analysis are summarized in Figures 3.7 and 3.8. Figure 3.7 indicates the salvage value (present value) of the demonstration satellite when the demonstration satellite is used as a source of power for other space activities such as GEO platforms, manufacturing bases, OTV or space exploration vehicles. The salvage value is shown as a function of the annual demand for space power and the cost of earth to GEO transportation. It can be seen that the salvage value is not materially impacted by transportation costs but is directly related to demand (MW/yr). At very high demand levels the salvage value can approach $150- 170 million and at a demand level of less than 1.5 MW/yr the salvage value is zero. It is possible that other major (nonpower) subsystems such as sliprings, mechanisms, transmitter subarray and switchgear and converters will be salvageable for other space missions. Figure 3.8 illustrates the salvage value of the SPS demonstration satellite when the power supply and several other major subsystems are salvageable. The salvage value is shown as a function of annual demand for power, the cost of earth-GEO transportation and the time (relative to * 2000) at which the nonpower subsystems are salvaged. Salvage value may approach $400 million when other subsystems are salvaged and the demand for It should be noted that certain of these curves terminate abruptly. For example, the curves for 20 year time delay terminate at a demand of 10 MW/yr indicating that the power subsystem would be completely segmented at the end of 20 years. It is assumed that other subsystems are not salvageable after the power supply is completely segmented. Definition Cumulative average learning rate for installing non-SPS power systen on mission spacecraft (%) Cumulative average learning rate for the annual cost of operating the demonstration satellite (%)
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