An integrated hybrid solar sail spacecraft architecture is disclosed, comprising a reflectivesail membrane equipped with reflectivity control devices (RCDs) for propellantless attitudeactuation; a distributed array of refractive concentrating optical elements supported by alow-density structural substrate disposed across the membrane; a routing pathway from theconcentrator focal regions to a centralized photovoltaic and power management module; alow-thrust electric propulsion stage powered by said module; one or more momentumstorage devices; and a control system that allocates attitude-management and desaturationduty between the reflectivity control devices and the electric propulsion stage so as tominimize propellant consumption subject to pointing-accuracy and power-budgetconstraints.The architecture addresses the demonstrated attitude-control bottleneck of prior-art solarsail spacecraft (IKAROS, LightSail-2, NEA Scout, ACS3) and increases the specific poweravailable to support electric propulsion through sail-integrated rather than bus-mountedconcentration optics. Applicable spacecraft classes include CubeSats (6U–27U), ESPA-classsmall satellites, and free-flying microsatellites operating in Earth-orbital, cislunar, andinterplanetary mission regimes.This deposit consists of the technical disclosure (disclosure.pdf, disclosure.md), a companionliterature review and patent prior-art landscape document (litrev.pdf, litrev.md), and fiveschematic figures (figures/fig1–fig5). The deposit serves as a defensive publicationestablishing public priority for the disclosed subject matter; a companion U.S. provisionalpatent application is being prepared for filing.
Gabriel Corradini Lourenço Dias (Tue,) studied this question.
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