A high temperature thermal protection systems for rockets, and associated methods, is disclosed. A representative system includes a launch vehicle having a first end and a second end generally opposite the first end. The launch vehicle is elongated along a vehicle axis extending between the first and second ends and carries a propulsion system having at least one nozzle positioned at the second end of the launch vehicle. A thermal protection apparatus positioned around the nozzle is used to provide cooling and/or insulation to the nozzle during the flight of the launch vehicle. The thermal protection apparatus can include multiple fabric layers and an insulation layer stacked and stitched together. The fabric layers can include metal alloy fibers. In representative systems, the thermal protection apparatus can further include provisions for water that saturates the insulation layer to provide further insulating and/or cooling effects.

A device and related method that provides, but is not limited thereto, a two-phase heat transfer device with unique combination of enhanced evaporation and increased cooling capacity. An advantage associated with the device and method includes, but is not limited thereto, increased cooling capacity per unit area, controlled and optimized evaporation, 10 prevention of boiling, and prevention of drying of the evaporator. An aspect associated with an approach may include, but is not limited thereto, using a non-wetting coating or structure to keep working fluid away from the spaces between elongated members of an evaporator and using a wetting coating or structure to form thin films of working fluid around the distal region of the elongated members.

A device and related method that provides, but is not limited thereto, a two-phase heat transfer device with unique combination of enhanced evaporation and increased cooling capacity. An advantage associated with the device and method includes, but is not limited thereto, increased cooling capacity per unit area, controlled and optimized evaporation, 10 prevention of boiling, and prevention of drying of the evaporator. An aspect associated with an approach may include, but is not limited thereto, using a non-wetting coating or structure to keep working fluid away from the spaces between elongated members of an evaporator and using a wetting coating or structure to form thin films of working fluid around the distal region of the elongated members.

An exterior panel for hypersonic transport vehicles is formed of a superplastic metal alloy such as titanium for accommodating high thermal stresses of hypersonic flight. The exterior panel, designed as re-usable on such transport vehicles, includes an exterior skin configured for atmospheric exposure, and an interior skin configured for attachment to structural frame members of the transport vehicles. An intermediate skin is situated between a pair of multicellular cores; each multicellular core is sandwiched between the exterior and interior skins, one core being situated between the exterior and intermediate skins, while the other is situated between the intermediate and interior skins. An airflow channel (AFC) extends through at least one of the multicellular cores for cooling of the exterior panel. Each multicellular core is superplastic formed and diffusion bonded to the other, as well as to its respective pair of skins to form an exterior panel having a unified structure.

A preceramic resin formulation comprising a polycarbosilane preceramic polymer, an organically modified silicon dioxide preceramic polymer, and, optionally, at least one filler. The preceramic resin formulation is formulated to exhibit a viscosity of from about 1,000 cP at about 25° C. to about 5,000 cP at a temperature of about 25° C. The at least one filler comprises first particles having an average mean diameter of less than about 1.0 μm and second particles having an average mean diameter of from about 1.5 μm to about 5 μm. Impregnated fibers comprising the preceramic resin formulation are also disclosed, as is a composite material comprising a reaction product of the polycarbosilane preceramic polymer, organically modified silicon dioxide preceramic polymer, and the at least one filler. Methods of forming a ceramic matrix composite are also disclosed.

This aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, is wherein it includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equipment.

This aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, is wherein it includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equipment.

A power supply device (104-1) includes a substrate (20) on which an electric component (25) is mounted, a chassis (10) having a chassis surface (11) and a threaded part (10a), a chassis-side resin part (91) connected to a back surface (20a) and the chassis surface (11), a fixation screw (29), and an insulating member (60). The fixation screw (29) fixes both the electric component (25) and the substrate (20) to the chassis (10) by screw-coupling an end part (29c) of the fixation screw (29), exposed in a direction toward the chassis (10) from an open hole formed through the insulating member (60), to the threaded part (10a) of the chassis (10). In addition, the fixation screw (29) brings the electric component (25) and the chassis (10) into electrical noncontact with each other by being placed in an open hole of the insulating member (60).

A system for controlling an aerospace vehicle by exploiting the dihedral effect to control bank angle of the vehicle by modulating sideslip. The control system includes a closed feedback loop comprising an outer loop for producing a sideslip angle command to induce a roll moment through the dihedral effect to satisfy a bank angle command, and an inner loop for taking the sideslip angle command, and possibly an angle of attack command to produce control input for flightpath hardware controls. Flightpath control hardware include pairs of flaps arranged longitudinally along the leading and trailing edges of an aeroshell of an aerospace entry vehicle to control pitch for changing the angle of attack, and another pair of flaps arranged laterally to control yaw for changing the bank angle via the sideslip angle, and also moving mass along ribs to control pitch and yaw. Thrusters can be fired to induce roll.

A lightweight ablator formulation has been developed which offers superior thermal performance compared to current state of the art ablator formulations. The lightweight ablator formulations described herein typically include at least one endothermically decomposing (energy absorbing) material with a fluxing agent resulting in significantly reduced backface temperature response and a more stable surface. According to one implementation the ablator composition comprises about 30 to about 70 percent by weight of a base silicone resin, about 25 to about 67 percent by weight of a low-density filler, about 3 to about 7 percent by weight of a curing agent and greater than 0 and up to about 10 percent by weight of a boron-containing compound.