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A Comparison of Nuclear and Chemical Propulsion Upper-Stage and Launch Systems for LEO to GEO Orbital Transfers
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Abstract
Comparisons are given between various launch vehicles, transfer vehicles, and propulsion methods to launch satellites into low Earth orbital parking orbits and then into a final geosynchronous orbit. The studies indicate that a Thermionic Space Nuclear Power System (TI-SNPS) can have significant advantages over solar array power systems for both orbital transfer capabilities and mission applications. Also, by utilizing a relatively inexpensive Atlas IIAS launch vehicle, a particular TI-SNPS hybrid design with a specific impulse of 950 sec can place a satellite weighing 3,511 kg into GEO orbit, as compared to only a corresponding 1,104 kg satellite capability when using conventional chemical propulsion techniques.
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Citation
Bailey, P. and Choong, P., "A Comparison of Nuclear and Chemical Propulsion Upper-Stage and Launch Systems for LEO to GEO Orbital Transfers," SAE Technical Paper 929505, 1992, https://doi.org/10.4271/929505.Also In
References
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