Abstract: Deployed equipment modules for satellite architecture improvement (DEMSAI) provide ample thermal radiator for area-limited small satellites that typically deploy large-area solar panels from a relatively small mainbody. Rectangular-box-shaped equipment modules are deployed from a compact stowed assembly to offer each of their six side panel exteriors as potential radiator area. Equipment packages are mounted to the interior of these panels. The resultant increase in radiator area translates to an increase in the power-handling capacity of small, fixed-body satellites without resort to deployed radiators.

Abstract: The wick-interrupt temperature controlling heat pipe (WITCH) is a device for controlling the temperature of spacecraft temperature-sensitive, heat dispensing devices. A heat transporting working fluid is conveyed in saturated equilibrium with its vapor across a discontinuous internal capillary liquid wick, within a tubular cylindrical pressure vessel, from a condenser section to an evaporator section located on either side of the discontinuity. When the temperature within the WITCH rises to a predetermined level, a sliding wick located within the internal capillary liquid wick is inserted across the discontinuity by a temperature sensitive control rod, thereby allowing the heat transporting working fluid to circulate from the condenser section wick to the evaporator section wick. In this configuration, the WITCH operates identically to the "constant-conductance heat pipe" commonly used.

Abstract: The package-interface thermal switch (PITS) is an active temperature cont device for modulating the flow of thermal energy from satellite equipment, such as electronic modules or batteries, to the satellite mounting deck which serves as a heat sink. PITS comprises a mounting bolt made of a shaped memory alloy (SMA) actuating bolt and a non-metallic rod with a helical spring surrounding it forming a mounting bolt for a satellite equipment package. At least four mounting bolts are used for installing the equipment package and are preloaded to a predetermined stress representing the desired thermal conductance between the heat sink and the package. The SMA actuating bolt is in thermal contact with the component or package and expands or contracts as the result of changing package temperature and the helical "return" spring forces against the SMA actuating bolt portion of the PITS, increasing ("hot-on" condition) or decreasing ("cold-off" condition) the pressure of the package against the mounting deck.

Abstract: The graphite-epoxy heat sink and mounting structure is comprised of a mounting structure constructed of a graphite-epoxy material that is mounted around a heat generating pressure vessel located inside a spacecraft. The mounting structure is a graphite-epoxy structure having three segments. The first and third segments are a graphite-epoxy material with a high thermal conductivity but not necessarily capable of withstanding structural stresses. Between these thermal conductive segments is a segment of graphite-epoxy material capable of withstanding structural stresses to provide a structural integrity for the mounting structure. The thermal energy flows from the pressure vessel, through the thermal conductive layer to a shear panel of the spacecraft that radiates the thermal energy.