Physics
Scientific paper
Jun 1993
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1993jpmc.confq....n&link_type=abstract
AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit, 29th, Monterey, CA, June 28-30, 1993, 7 p.
Physics
Interstellar Space, Ion Propulsion, Nuclear Electric Propulsion, Space Exploration, Thermoelectric Generators, Mission Planning, Orbital Rendezvous, Payload Delivery (Sts), Rocket Thrust, Specific Impulse
Scientific paper
A means of propelling small scientific payloads on a regular basis to the outer Solar System and interstellar space is explored. Small payloads would encourage more frequent deep-space missions and faster response to changing scientific needs. High specific impulse, electric propulsion allows large payload fractions to be delivered if an adequate space power source exists. Radioisotope electric propulsion (REP) offers a simple, reliable and immediately available method for propelling 50 to 100 kilogram payloads into deep-space with existing 100 to 1000 Watt thermoelectric generators and ion engines. The perceived liability of radioisotope electric generators for ion propulsion is their high specific mass (mass per unit power). To investigate the efficacy of using high specific mass powerplants, a numerical study of low-thrust heliocentric trajectories and flight times was performed. Rendezvous flights between the Earth and outer planets and interstellar precursor missions in the ecliptic plane beyond the heliopause (100 AU) were considered. Powerplant specific masses of 200, 100, 50 and 20 kg/kW and payload ratios of 0, 0.25 and 0.5 were used to determine the dependence of flight time on these important parameters. The conclusions are that heliocentric flight time is a weak function of the powerplant specific mass, and that regularly scheduled small scientific missions can be initiated with a specific mass of about 100 kg/kW.
Noble Robert J.
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