This study illuminates problems to be encountered when electrostatic colloid propulsion is integrated with operational spacecraft. The study method is to hypothetically apply colloid propulsion to four spacecraft: Program 191, a spinning satellite; Low Altitude Surveillance Satellite on which the colloid system performs drag make-up; ATS-G which exposes problems of compatibility with a complex experimental spacecraft; and Program 621-B which provides opportunity to study a multi-function, multi-thruster system. The study was conducted in three main tasks with the following conclusions: In comparison with alternate forms of propulsion, colloid propulsion is flexible in its adaptability to a variety of missions for which its low thrust, high specific impulse, and low power are uniquely suited; the impact on the development program of a spacecraft using colloid propulsion is that time spans need not be expanded provided that adequate effort is expended in planning and testing to insure proper integration; attention must be given to interface interactions between the colloid system and most other spacecraft equipment items. (Author)


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