Jupiter explorer using microspacecraft and bimodal reactor system
- California Inst. of Tech., Pasadena, CA (United States). Jet Propulsion Lab.
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, 1,000 N thrust, 850 s Isp, with a 1,500 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 its satellites with 11 microspacecraft. This bimodal reactor system produces 1,000 N of thrust at an Isp of 850 s using hydrogen propellant, 1,880 N of thrust at an Isp of 450 s using NH3 propellant. The electric propulsion subsystem consists of ion engines using Xenon propellant with a specific impulse of 5,000 s and a specific mass of 18 kg/kWe. Hydrogen tanks are assumed to have a dry mass equal to 15% of the propellant they contain.
- OSTI ID:
- 435531
- Report Number(s):
- CONF-960805--
- Country of Publication:
- United States
- Language:
- English
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