Figure VI-5.- LEO-to-GEO transfer time as a function of thrust/weight. unresolved and directly affecting the cost competitiveness of this approach, include the following. 1. Thruster efficiency and specific jet power 2. Thruster specific impulse 3. Thruster refurbishment and total operating life 4. Nuclear reactor disposal after useful life 5. Allowable orbit transfer time The configuration and construction concept that allows the SPS to be at least partially assembled in LEO allows the COTV|_ to use payload-supplied power. Its structural acceleration limits are expected to be so low (0.001g or less) that the low thrust level orbital mechanics computations are necessary. The COTV|_ candidates are primarily defined by the characteristics of their thrusters. At this time, an MPD arcjet configuration has been identified as the "best case" option, with the electrically driven thermal arcjet as the fallback position, or "worst case" option.
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