J. C. Hooper Propulsion & Power Div. d. Reaction Control System The annual impulse requirements are summarized below for the column/cable configuration. It is assumed that inclination will be held at zero and mean longitude held constant, and that periodic eccentricity variations will not be counteracted. Mass is assumed to be 90 x 106 kg. Thrust level was set at 335 N at each of 16 locations (see figure IV-B-4-2) to provide adequate control authority. In-depth study of the requirements might reduce this figure substantially. Several electric propulsion options were evaluated and are summarized in table IV-B-4-1. The candidate systems considered were electrostatic (ion) thrusters, magnetoplasmadynamic (MPD)-arc jet thrusters, thermal arc jet thrusters, and an 02/H2 chemical thruster system in which the propellants are produced electrolytically from water. For each of these systems, the required electrical power was assumed to be supplied by the satellite. This group of systems in not, and is not intended to be, an inclusive list of all viable systems for performing the RCS functions for the power satellite. It is quite possible that a system not considered could be more desirable from an overall standpoint than any of those presented here. These systems do represent a range of electric propulsion options insofar as weight, performance, and power requirements are concerned. For the systems discussed, further study may indicate the desirability of operation at other than the maximum Isp conditions (as assumed here), with an attendant reduction in power requirements and number of thrusters.
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