II. EMISSION MODELS In the present section, we attempt to describe the characteristics of the SPS injectants in the magnetosphere. The description is limited to the determinable quantitative parameters from the reference system report of the SPS concept development program (U.S. DOE, 1979) and the SPS Baseline Review (U.S. NASA, 1978). The evolution of each injectant in the magnetosphere is not considered in this section, because the evolution is properly the magnetospheric effect itself. Even for this limited task at hand, we have found that the information available is not sufficient for us to completely evaluate the impacts on specific physical processes. This is particularly true in regard to thrusting schedules. We have attempted to supplement the basic information with some consideration of rocket dynamics. The primary sources of matter and energy injected into the magnetosphere are ionized argon exhaust from the solar-powered cargo orbit transfer vehicles (COTV) that ferry the payload between LEO and GEO, and neutral chemical exhaust in the form of H2O and H2 (or H and 0 atoms after photodissociation) from the personnel orbit transfer vehicles (POTV). In addition, the COTV may also use subsidiary chemical engines and the SPS spacecraft in its operational form may use argon ion (Ar+) engines for station-keeping activities. Because of this simple breakdown into two key elements of magnetospheric injection and because the present assessment effort is not expected to represent a complete scaling-up of physical phenomena to SPS dimensions, we shall consider the emissions in terms of output from a single SPS mission, rather than a sequence of SPS missions. Accumulative effects will be considered separately. 4
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