Design and Performance Characteristics for Low Power Space Reactor Systems

Abstract

Several missions requiring electrical power in the 10 to 40 kW range have been identified as potential applications for a space reactor power system which uses the technology currently being developed under the SP-100 Ground Engineering System (GES) Program. The conceptual designs proposed for these low power applications build upon these key GES technologies, thereby maximizinjg the potential applicability of this development effort by fully utilizing the inherent scalability of the design implementations defined as elements of the 100 kW, Generic Flight System.Design and performance characteristics are provided for a specific point design with a 10 kW rated electrical output. While retaining the: major attributes of this design, the system power rating is scaled over the power range h m 10 to 40 kW, and important spacecraft integration parameters, such as total mass and radiator area, are presented as a function of allowable self-generated radiation dose at the payload interface plane and separation distance between this plane and the reactor core.

Design study of PbBi- and NaK-cooled small deep sea fast reactors

“…8(a) has been proposed for a space reactor with the electric power up to 20 kWe (Shepard et al, 1991). The thermal efficiency of a thermoelectric power converter used in the space reactor is 5% (Shepard et al, 1990). If we use a dynamic power converter such as the closed Brayton cycle, an electric power up to 80 kWe can be obtained from the core because of its higher thermal efficiency.…”