Abstract: A system and method for generating electrical power from a solar power supply using at least one concentrator array having a plurality of photovoltaic cells and corresponding reflector groups to direct light to the photovoltaic. A concentration ratio indicative of a portion of the electrical power capacity to generate to power a spacecraft is determined. The concentration ratio is communicated to a control module on the concentrator array. The control module selects a number of reflectors from the total number of reflectors to orient into a photovoltaic energizing position, where the selected number of reflectors corresponds to a concentration ratio of the total number of reflectors.

Abstract: A system and method for generating electrical power from a solar power supply using at least one concentrator array having a plurality of photovoltaic cells and corresponding reflector groups to direct light to the photovoltaic. A concentration ratio indicative of a portion of the electrical power capacity to generate to power a spacecraft is determined. The concentration ratio is communicated to a control module on the concentrator array. The control module selects a number of reflectors from the total number of reflectors to orient into a photovoltaic energizing position, where the selected number of reflectors corresponds to a concentration ratio of the total number of reflectors.

Abstract: A flexible space structure such as a solar array is composed of multiple solar cell modules (SCMs) each supporting an arrangement of solar cells on a frontside layer and incorporating a backside layer with a surface opposite from the frontside layer having a conductive coating. A selected portion of the SCMs have structural ground extension harnesses intermediate the frontside layer and backside layer. Conductive tapes secure vertically adjacent SCMs by attachment to the conductive coating and electrical jumpers interconnect the structural ground extension harnesses across gapped hinge lines of laterally adjacent SCMs.