TABLE 7-8. PHOTOVOLTAIC SOLAR POWER SATELLITE FUEL CONSUMPTIONS (Z-AXIS SOLAR ORIENTATION) Note: Specific Impulse = 714 Ns kg-1. The two total estimates differ in the concept for station keeping in the presence of solar pressure. The greater value results from complete compensation of the solar pressure by the RCS. The smaller value was obtained by assuming that the cyclical orbit eccentricity with a period of approximately 1 year was not corrected, but the more critical orbit period was corrected. The alternate orientation of X-POP requires approximately 274 000 kg/year of propellant to compensate for gravity gradient torques. A systems tradeoff analysis was made using the systems design analysis model for two X-POP and one Z-solar orientation concepts. In one X-POP case the array area was increased approximately 4 percent to compensate for solar angle-of-incidence losses to give an average output of 10 GW. The other X-POP case was for a minimum output of 10 GW in which the array area was increased approximately 8 percent. Output for the Z-solar case was a constant 10 GW since the array was maintained perpendicular to the solar
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