This invention is a solar-powered space system configured to reduce or eliminate resistive losses during high-current DC power delivery using its superconducting power distribution combined with passive radiative cooling and a working fluid thermal loop. Background: Solar photovoltaic arrays, which generate direct current (DC) power, are the primary electrical power source for spacecraft, satellites, and space-based computing. DC power transmission involves large currents, which result in non-negligible resistive losses in the wiring, connectors, and bus structures. In space, these losses mainly manifest as heat that must then be rejected through radiative cooling. In larger systems, wiring losses become more significant and add to the total thermal load, which then increases the required radiator area, mass, and complexity. Current solutions reduce these losses by increasing bus voltage, but at the expense of insulation, arcing risk, and power-conversion overhead. Superconducting conductors offer negligible resistance but must be operated below a critical temperature, which often makes them difficult to integrate into large space platforms. This invention uses radiative cooling to allow the superconductors to operate below their critical temperature and offer negligible resistive losses. Applications:
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