Abstract
Solar electric propulsion (SEP) is currently being studied for possible use in a number of near-Earth and planetary missions. Thruster systems for these missions could be integrated directly into a spacecraft or modularized into a thruster subsystem module (TSSM). A TSSM for electric propulsion missions would consist of a 30-cm ion thruster, thruster gimbal system, propellant storage and feed system, associated power processing unit (PPU), thermal control system, and complete supporting structure. The TSSM would be wholly selfcontained and be essentially a plug-in or strap-on electric stage with simple mechanical, thermal, electrical, and propellant interfaces. The TSSM described is designed for a broad range of missions requiring from 2 to 10 TSSM's mounted in a 2 by jc configuration. The thermal control system is designed to accommodate waste heat from the power processors based on realistic efficiencies when the TSSM is operating from 0.7 to 3.5 a.u. The modules are 0.61 m (2 ft) wide by 2.29 m (7.5 ft) long and have a dry weight including propellant tank of 54.4 kg (120 Ib). The propellant tank will hold 145.1 kg (320 Ib) of mercury.
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