which have had extensive development for terrestrial applications. Electricity is produced by means of a closed Brayton cycle (CBC) engine, the power conversion unit (PCU), located behind the solar receiver cavity. The solar cavity receives concentrated solar energy from a parabolic reflector. A solar dynamic radiator (SDR) rejects the waste heat from SDPM-PCU and electronics to the space station orbital environment. The low natural frequency of the baseline SDR for this configuration potentially compromises the ability to the fine pointing and tracking (FP&T) control system to meet a 0.1 degree pointing accuracy requirement. In order to achieve a higher natural frequency in the design of the SDR, three alternative configurations that meet this requirement have been studied by the Rocketdyne and LTV Missiles and Electronics Group. These options included a modified baseline vertical configuration and two alternatives known as ‘bow-tie' and ‘butterfly' configurations. This paper analyzes the three alternatives to the baseline radiator configuration and discusses their merits based on space shuttle cargo capabilities, location with respect to the SDPM supporting structure, thermal performance, drag, concentrator shading, mass and other issues of concern. Results indicating the advantages and disadvantages of each option are presented. Solar Dynamic Power Module Cycle Description The SDPM is comprised of three major elements: the solar concentrator, the power generation subsystem (PGS) and the heat rejection assembly. The PGS includes the
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