Application of a SNTP-Based Propulsion/Power System to Solar System Exploration Missions

Details Application of a SNTP-Based Propulsion/Power System to Solar System Exploration Missions Application of a SNTP-Based Propulsion/Power System to Solar System Exploration Missions

Jul 1994

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1994aipc..301...45v&link_type=abstract

SPACE NUCLEAR POWER AND PROPULSION: Eleventh Symposium. AIP Conference Proceedings, Volume 301, pp. 45-53 (1994).

Computer Science

Performance

Scientific paper

A ``bi-modal'' nuclear propulsion and power system based on the United States Air Force's (USAF's)* Space Nuclear Thermal Propulsion (SNTP) technology is applied to a set of high energy Solar system exploration missions. Performance comparisons are made to a baseline mission set developed by the Jet Propulsion Laboratory utilizing a nuclear electric propulsion system based on the SP-100 space power system. Orbiters and probes of Uranus, Neptune, and Pluto, a Grand Tour of the Galilean moons of Jupiter, a Comet Nucleus Sample Return, and a Multiple Mainbelt Asteroid Rendezvous mission are analyzed. The first five missions utilizing SP- 100 required a Shuttle-C or equivalent heavy lift launcher. With the bi-modal PBR system, the payload goals are deliverable in the same transit times, but on the smaller, existing Titan IV launcher. Furthermore, all optional payloads originally available only at increased transit time are accommodated. Available mass margins for these missions are 20%-85% of the power/propulsion system mass, providing significant robustness. The same missions were analyzed on a Titan III launcher in order to pursue further cost reductions. Substantial payload masses (1000 kg or more) were found to be available in all cases with reasonable transit times, coinciding well with the current ``lighter, faster, cheaper'' NASA philosophy.

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