Abstract: A novel heat management system for aircraft is provided which is based on the aircraft fuel as the heat exchange medium and comprises a dedicated thermal reserve fuel tank for containing refrigerated aircraft fuel (or other expendable liquid) which is cooled by heat exchange with the primary aircraft fuel flow to the engines, a fuel line loop for conducting fuel through a plurality of heat exchangers associated with cooling loops for heat generating aircraft systems, and a central microprocessor based controller for controlling fuel flow and temperature throughout the fuel loop system and into the aircraft engine.

Abstract: An improved printed circuit board housing assembly is described wherein localized high intensity cooling of heat dissipating electronic components mounted on the circuit boards may be accomplished by direct impingement of streams of fluid coolant onto individual components; when coolant is passed through the housing, fluid streams, generated at openings provided in the circuit boards, impinge onto electronic components mounted on the next circuit board downstream from the source of coolant flow.

Abstract: A heat pipe or thermosiphon device is provided which may be configured for operation in various temperature regimes from cryogenic to elevated temperatures and in gravity or other orientation sensitive environments, as well as zero-gravity or other orientation insensitive environments. The invention comprises a heat pipe, containing a magnetically susceptible liquid as the working fluid, surrounded by an electro-magnet or permanent magnet which produces a magnetic field gradient which interacts with the magnetically susceptible liquid to produce an artificial body force field analogous to, but which may be substantially greater than, the gravitational force field, for separation of the liquid from gaseous phases of the magnetically susceptible working fluid within the heat pipe.