Implementing magnetic shielding has application across the spectrum of thruster power and sizes and is therefore a cross-cutting technology. The thruster will be well suited for orbit raising and interplanetary transfers, supporting exploration and science missions. The demonstrated throttling ability is important for a singular thruster that might be called upon to propel a spacecraft from Earth to Mars or Venus. Mars orbits at 1.52 AU, which reduces the solar constant to 43% of the value at Earth. As a result the output power of a nominal 600 W array reduces to 260 W at Mars as a spacecraft travels between these planets. For NASA low power, high throughput electric propulsion systems are an enabling technology for radio isotope powered spacecraft for sample and return missions identified in the NASA Decadal Survey. A study conducted by the SMD ISPT Project in 2004 confirmed the significant potential of REP for space science, especially with recent advancements in enabling, high –specific-power RPS technology (from 3 to over 8 We/kg). The study also concluded that REP would be ready for near-term NASA science missions if an electric propulsion thruster with the appropriate specific impulse and propellant throughput capability could be developed. Examples of missions examined by this study include: 1) Trojan Asteroid Orbiters, 2) Jupiter Polar Orbiter with probes and 3)Comet Surface Sample Return (Tempel 1)
Commercial applications for the proposed system include orbit raising, circularization, inclination changes, repositioning, and station-keeping. For higher power missions, the system would be clustered. Commercial applications for a clustered system include a small electric upper-stage. Other applications include a system for de-orbiting spacecraft that have reached their end of life.
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