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 energy storage reservoir positioned within the vapor chamber contains a phase change material for absorbing thermal energy.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.

A hypersonic aircraft includes one or more leading edge assemblies that are designed to cool the leading edge of certain portions of the hypersonic aircraft that are exposed to high thermal loads, such as extremely high temperatures and/or thermal gradients. Specifically, the leading edge assemblies may include an outer wall tapered to a leading edge or stagnation point. A coolant supply provides a flow of cooling fluid to a porous tip that is joined to the forward end of the outer wall and defines variable porosity and/or internal barriers to direct a flow of cooling fluid to the regions of the leading edge experiencing the highest thermal loading.

A method and apparatus for a boundary layer control device located relative to an aircraft structure. The boundary layer control device has a stowed position and a deployed position. The boundary layer control device moves from the stowed position to the deployed position. A thickness of a boundary layer for the aircraft structure increases in a manner that increases a distance of a heat flow field from the aircraft structure during operation of the aircraft.

A method and apparatus for a boundary layer control device located relative to an aircraft structure. The boundary layer control device has a stowed position and a deployed position. The boundary layer control device moves from the stowed position to the deployed position. A thickness of a boundary layer for the aircraft structure increases in a manner that increases a distance of a heat flow field from the aircraft structure during operation of the aircraft.

A fluid interaction apparatus includes a wing having a first configuration with a first profile drag coefficient and a second configuration with a second profile drag coefficient that is less than the first profile drag coefficient. The fluid interaction apparatus further includes a body having a longitudinal axis, wherein the body is coupled to the wing. The fluid interaction apparatus further includes an actuator configured to change the wing from the first configuration when moving in a first direction relative to the body to the second configuration when moving in a second direction relative to the body, the second direction having a substantial component parallel to the longitudinal axis of the body.

A fluid interaction apparatus includes a wing having a first configuration with a first profile drag coefficient and a second configuration with a second profile drag coefficient that is less than the first profile drag coefficient. The fluid interaction apparatus further includes a body having a longitudinal axis, wherein the body is coupled to the wing. The fluid interaction apparatus further includes an actuator configured to change the wing from the first configuration when moving in a first direction relative to the body to the second configuration when moving in a second direction relative to the body, the second direction having a substantial component parallel to the longitudinal axis of the body.

An impingement cooling system is disclosed, including an airfoil having an aerodynamically sharp leading edge, a fluid source, and a fluid dispersal device connected to the fluid source. The leading edge has a concave internal surface and the fluid dispersal device is configured to project a fluctuating stream of fluid toward the internal surface.

An aircraft structure, comprising a heat shield including. The heat shield includes an interior; a skin enclosing the interior; a plurality of barriers attached in the interior to the skin, each of the barriers spaced to separate a plurality of thermal insulation layers disposed in the interior; and wherein the barriers suppress heat flow between the thermal insulation layers.

An aircraft structure, comprising a heat shield including. The heat shield includes an interior; a skin enclosing the interior; a plurality of barriers attached in the interior to the skin, each of the barriers spaced to separate a plurality of thermal insulation layers disposed in the interior; and wherein the barriers suppress heat flow between the thermal insulation layers.