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An integral space power concept provides both the electrical power and propulsion from a common heat source and offers superior performance capabilities over conventional orbital insertion using chemical propulsion systems. This paper describes a hybrid (bimodal) system concept based on a proven, inherently safe solid fuel form for the high temperature reactor core operation and rugged planar thermionic energy converter for long-life steady state electric power production combined with NERVA-based rocket technology for propulsion. The integral system is capable of long-life power operation and multiple propulsion operations. At an optimal thrust level, the integral system can maintain the minimal delta-V requirement while minimizing the orbital transfer time. A trade study comparing the overall benefits in placing large payloads to GEO with the nuclear electric propulsion option shows superiority of nuclear thermal propulsion.

A hybrid space nuclear reactor which can provide both electrical power and thermal propulsion has been found to have significant benefits for near term military satellites. It combines the STAR-C thermionic reactor with NERVA rocket propulsion technology. This hybrid reactor would use a W/UO2 cermet core which was developed in the nuclear rocket program of the 1960's. Both the reactor core and the thermionic converters can be tested prior to launch. The design of a 10 kWe reactor capable or producing over 1300 N of thrust is described.