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Nuclear bimodal new vision solar system missions

Journal Article · · AIP Conference Proceedings
DOI:https://doi.org/10.1063/1.50044· OSTI ID:385460
 [1];  [2]
  1. Jet Propulsion Laboratory, California Institute of Technology, Pasadena, California 91109-8099 (United States)
  2. Lockheed Martin Corp., Lockheed Martin Astronautics, Denver, Colorado 80201 (United States)

This paper presents an analysis of the potential mission capability using space reactor bimodal systems for planetary missions. Missions of interest include the Main belt asteroids, Jupiter, Saturn, Neptune, and Pluto. The space reactor bimodal system, defined by an Air Force study for Earth orbital missions, provides 10 kWe power, 1000 N thrust, 850 s Isp, with a 1500 kg system mass. Trajectories to the planetary destinations were examined and optimal direct and gravity assisted trajectories were selected. A conceptual design for a spacecraft using the space reactor bimodal system for propulsion and power, that is capable of performing the missions of interest, is defined. End-to-end mission conceptual designs for bimodal orbiter missions to Jupiter and Saturn are described. All missions considered use the Delta 3 class or Atlas 2AS launch vehicles. The space reactor bimodal power and propulsion system offers both; new vision {open_quote}{open_quote}constellation{close_quote}{close_quote} type missions in which the space reactor bimodal spacecraft acts as a carrier and communication spacecraft for a fleet of microspacecraft deployed at different scientific targets and; conventional missions with only a space reactor bimodal spacecraft and its science payload. {copyright} {ital 1996 American Institute of Physics.}

OSTI ID:
385460
Report Number(s):
CONF-960109--
Journal Information:
AIP Conference Proceedings, Journal Name: AIP Conference Proceedings Journal Issue: 1 Vol. 361; ISSN 0094-243X; ISSN APCPCS
Country of Publication:
United States
Language:
English