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 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.

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 system for removing heat from an aircraft component includes: a heat exchanger in proximity to an aircraft component and having an inlet, an outlet, and an internal surface coated with a catalyst; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system. A method of removing heat from an aircraft component includes providing a heat exchanger in proximity to an aircraft component, the heat exchanger being in fluid communication with a source of hydrocarbon fuel and a source of water and having an internal surface coated with a catalyst; introducing a hydrocarbon fuel into the heat exchanger; introducing oxygen into the heat exchanger; contacting the hydrocarbon fuel with the catalyst; and cracking the hydrocarbon fuel.

A system for removing heat from an aircraft component includes: a heat exchanger in proximity to an aircraft component and having an inlet, an outlet, and an internal surface coated with a catalyst; a source of hydrocarbon fuel in fluid communication with the inlet of the heat exchanger; a source of oxygen in fluid communication with the inlet of the heat exchanger; and a distribution system. A method of removing heat from an aircraft component includes providing a heat exchanger in proximity to an aircraft component, the heat exchanger being in fluid communication with a source of hydrocarbon fuel and a source of water and having an internal surface coated with a catalyst; introducing a hydrocarbon fuel into the heat exchanger; introducing oxygen into the heat exchanger; contacting the hydrocarbon fuel with the catalyst; and cracking the hydrocarbon fuel.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to manage thermal loads experienced at the leading edges during high speed or hypersonic operation. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. The outer wall may define a vapor chamber and a capillary structure within the vapor chamber for circulating a working fluid in either liquid or vapor form to cool the leading edge. In addition, a thermal enhancement feature can enhance a heat transfer from the outer wall at the leading edge to the outer wall within the condenser section of the vapor chamber.

A leading edge assembly for a hypersonic vehicle is provided. The leading edge assembly includes an outer wall that tapers to a leading edge, the outer wall having a porous region at the leading edge; a coolant supply assembly in fluid communication with the porous region for selectively providing a flow of coolant through the porous region of the outer wall; and an insulation layer disposed between a portion of the coolant supply assembly and the outer wall, wherein the insulation layer is configured to reduce heat transfer between the coolant supply assembly and the outer wall.

A leading edge assembly for a hypersonic vehicle is provided. The leading edge assembly includes an outer wall that tapers to a leading edge, the outer wall having a porous region at the leading edge; a coolant supply assembly in fluid communication with the porous region for selectively providing a flow of coolant through the porous region of the outer wall; and an insulation layer disposed between a portion of the coolant supply assembly and the outer wall, wherein the insulation layer is configured to reduce heat transfer between the coolant supply assembly and the outer wall.