Jupiter explorer using microspacecraft and bimodal reactor system

Using second generation microspacecraft and space reactor bimodal systems enables having a fleet of microspacecraft throughout the Jovian Planetary System simultaneously obtaining scientific data of Jupiter and its satellites. The microspacecraft uses new micro-technology and each spacecraft has a dry mass of 10 to 20 kg as described by Collins, et al. (1995). The space reactor bimodal system, defined by an Air Force study for Earth orbital missions and reported by Weitzberg, et al. (1995), provides 10 kWe power, 1000 N thrust, 850 s Isp, with a 1500 kg system mass. Using this bimodal system, trajectories to Jupiter were examined and an optimal direct and gravity assisted trajectory selected as described by Zubrin and Mondt (1996). A conceptual design for a spacecraft using the space reactor bimodal system for propulsion and power, that is capable of performing the Jupiter mission of interest, is defined. An end-to-end example mission is defined for Jupiter and it satellites with 11 microspacecraft. An Atlas 2AS launch vehicle is used to launch the bimodal spacecraft and its payload into Earth orbit. The space reactor propulsion system is then used with Earth gravity assists to place the spacecraft and eleven second generation microspacecraft from Earth orbit into a Jupiter orbit. The space reactor bimodal spacecraft acts as a carrier and communication spacecraft for a fleet of microspacecraft. This fleet of microspacecraft act in a coordinated manner and gather science data from several scientific target in the Jovian planetary system.