A method includes obtaining thermal energy from a structure to be cooled, where the structure includes micro-channels. The method also includes providing the thermal energy to a water-based polymer network, where the water-based polymer network includes a gel formed using a polymer and water. The method further includes generating one or more gases by heating the water-based polymer network, where generating the one or more gases includes releasing the water in the water-based polymer network to produce steam. In addition, the method includes passing the one or more gases through the micro-channels to remove at least some of the thermal energy from the structure.

A thermal insulation system for an aircraft is provided. The thermal insulation system includes a carrier and a container. The carrier has an interior surface including a first plurality of magnets that generate a first magnetic field, and an exterior surface that is thermally coupled to at least one high temperature component. The container is surrounded by the interior surface of the carrier, has an exterior surface including a second plurality of magnets that generate a second magnetic field oriented opposite the first magnetic field, and has an interior surface that is thermally coupled to at least one temperature sensitive component. The first magnetic field and the second magnetic field generate a gap between the carrier and the container to reduce a heat transfer from the at least one high temperature component to the at least one temperature sensitive component during operation of the aircraft.

A thermal insulation system for an aircraft is provided. The thermal insulation system includes a carrier and a container. The carrier has an interior surface including a first plurality of magnets that generate a first magnetic field, and an exterior surface that is thermally coupled to at least one high temperature component. The container is surrounded by the interior surface of the carrier, has an exterior surface including a second plurality of magnets that generate a second magnetic field oriented opposite the first magnetic field, and has an interior surface that is thermally coupled to at least one temperature sensitive component. The first magnetic field and the second magnetic field generate a gap between the carrier and the container to reduce a heat transfer from the at least one high temperature component to the at least one temperature sensitive component during operation of the aircraft.

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35 C. to 1,650 C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

A concentric, double hull, damage tolerant airframe vehicle double clad with a lightweight, impact resistant ceramic matrix composite for heat shielding and flame resistance, and fitted with insulation, to provide thermal protection from 35 C. to 1,650 C. of the internal fuselage areas for an extended period of time within an extreme heat environment, that will serve as a semi or fully autonomous vehicle, manned or unmanned, preferably an unmanned aerial vehicle designed as the delivery means to suppress or extinguish flames by repeatedly discharging pressure waves against flames without having to exit the fire environment.

An aircraft propulsion system with a drag reduction portion adapted to reduce skin friction on at least a portion of the external surface of an aircraft. The drag reduction portion may include an inlet to ingest airflow. The aircraft may also have an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

An aircraft propulsion system with a drag reduction portion adapted to reduce skin friction on at least a portion of the external surface of an aircraft. The drag reduction portion may include an inlet to ingest airflow. The aircraft may also have an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

An aircraft propulsion system with a drag reduction portion adapted to reduce skin friction on at least a portion of the external surface of an aircraft. The drag reduction portion may include an inlet to ingest airflow. The aircraft may also have an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

An aircraft propulsion system with a drag reduction portion adapted to reduce skin friction on at least a portion of the external surface of an aircraft. The drag reduction portion may include an inlet to ingest airflow. The aircraft may also have an internally cooled electric motor adapted for use in an aerial vehicle. The motor may have its stator towards the center and have an external rotor. The rotor structure may be air cooled and may be a complex structure with an internal lattice adapted for airflow. The stator structure may be liquid cooled and may be a complex structure with an internal lattice adapted for liquid to flow through. A fluid pump may pump a liquid coolant through non-rotating portions of the motor stator and then through heat exchangers cooled in part by air which has flowed through the rotating portions of the motor rotor. The drag reduction portion and the cooled electric motor portion may share the same inlet.

An apparatus and method that improves the operation of aerospace planes or rockets having an integrated flute and hat components whereby the flute functions as a hypersonic refrigeration engine and the hat as a flat plate heat exchanger to achieve an isothermal compression of the incipient hypersonic air in front of the nosecone to reduce hypersonic vibrations during flight, these improvements allow for the reduction in temperature during flight operation allowing for improved cooling of the aerospace plane or rocket.