Abstract: Methods and apparatus for cooling a surface on a flight vehicle and generating power include advancing the vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A first working fluid circulates through a first fluid loop that heats the first working fluid through a first heat intake thermally coupled to the surface and expands the first working fluid in a first thermal engine to generate a first work output. A second fluid loop has a second working fluid that receives heat from the first working fluid and a second thermal engine to generate a second work output. The first and second work outputs are operably coupled to first and second generators, respectively, to power primary or auxiliary systems on the flight vehicle.

Abstract: Methods and apparatus for cooling a surface on a flight vehicle and/or generating power include advancing the flight vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A supercritical working fluid is circulated through a fluid loop that includes compressing the supercritical working fluid through a compressor, heating the supercritical working fluid through a heat intake that is thermally coupled to the surface, expanding the supercritical working fluid in a thermal engine to generate a work output, cooling the supercritical working fluid, and recirculating the supercritical working fluid to the compressor. The work output of the thermal engine is operably coupled to the compressor, and may optionally be coupled to a generator to produce power. The supercritical working fluid absorbs heat from the surface, eliminating hot spots and permitting use of lighter and/or less expensive materials.

Abstract: Methods and apparatus for cooling a surface on a flight vehicle and generating power include advancing the vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A first working fluid circulates through a first fluid loop that heats the first working fluid through a first heat intake thermally coupled to the surface and expands the first working fluid in a first thermal engine to generate a first work output. A second fluid loop has a second working fluid that receives heat from the first working fluid and a second thermal engine to generate a second work output. The first and second work outputs are operably coupled to first and second generators, respectively, to power primary or auxiliary systems on the flight vehicle.

Abstract: A heat transfer device includes a storage chamber, a coolant housed within the storage chamber, a cooling chamber, one or more heat transfer components, a fluid passage between the storage chamber and the cooling chamber, and a barrier element. The one or more heat transfer components facilitate heat transfer from a heat source outside of the cooling chamber to the cooling chamber. The barrier element may have (i) a closed configuration, and (ii) an open configuration in which the barrier element is configured to allow the coolant in the storage chamber to flow from the storage chamber into the cooling chamber. The barrier element may reconfigure from the closed configuration to the open configuration in response to a trigger condition, such as the coolant housed within the storage chamber reaching a trigger temperature and/or the initial pressure of the coolant housed within the storage chamber reaching a trigger pressure.

Abstract: Methods and apparatus for cooling a surface on a flight vehicle and/or generating power include advancing the flight vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A supercritical working fluid is circulated through a fluid loop that includes compressing the supercritical working fluid through a compressor, heating the supercritical working fluid through a heat intake that is thermally coupled to the surface, expanding the supercritical working fluid in a thermal engine to generate a work output, cooling the supercritical working fluid, and recirculating the supercritical working fluid to the compressor. The work output of the thermal engine is operably coupled to the compressor, and may optionally be coupled to a generator to produce power. The supercritical working fluid absorbs heat from the surface, eliminating hot spots and permitting use of lighter and/or less expensive materials.

Abstract: A heat transfer device includes a storage chamber, a coolant housed within the storage chamber, a cooling chamber, one or more heat transfer components, a fluid passage between the storage chamber and the cooling chamber, and a barrier element. The one or more heat transfer components facilitate heat transfer from a heat source outside of the cooling chamber to the cooling chamber. The barrier element may have (i) a closed configuration, and (ii) an open configuration in which the barrier element is configured to allow the coolant in the storage chamber to flow from the storage chamber into the cooling chamber. The barrier element may reconfigure from the closed configuration to the open configuration in response to a trigger condition, such as the coolant housed within the storage chamber reaching a trigger temperature; and/or the initial pressure of the coolant housed within the storage chamber reaching a trigger pressure.