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 may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.

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 may be in fluid communication with at least one fluid passageway that passes through the outer wall to deliver a flow of cooling fluid, such as liquid metal, to the stagnation point. The liquid metal vaporizes when the leading edge experiences a high heat load, thereby transpiration cooling the leading edge and/or facilitating a magnetohydrodynamic process for generating thrust or electricity.

Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

Some variations provide a leading-edge heat pipe comprising: (a) an envelope fabricated from a shell material, wherein the envelope includes at least one edge with a radius of curvature of less than 3 mm, and wherein the envelope includes, or is in thermal communication with, at least one heat-rejection surface; (b) a porous wick fabricated from a ceramic or metallic wick material, wherein the porous wick is configured within a first portion of the interior cavity, wherein at least a portion of the porous wick is adjacent to the inner surface, and wherein the porous wick has a bimodal pore distribution comprising an average capillary-pore size from 0.2 microns to 200 microns and an average high-flow pore size from 100 microns to 2 millimeters (the average high-flow pore size is greater than the average capillary-pore size); and (c) a phase-change heat-transfer material contained within the porous wick.

Some variations provide a leading-edge heat pipe comprising: (a) an envelope fabricated from a shell material, wherein the envelope includes at least one edge with a radius of curvature of less than 3 mm, and wherein the envelope includes, or is in thermal communication with, at least one heat-rejection surface; (b) a porous wick fabricated from a ceramic or metallic wick material, wherein the porous wick is configured within a first portion of the interior cavity, wherein at least a portion of the porous wick is adjacent to the inner surface, and wherein the porous wick has a bimodal pore distribution comprising an average capillary-pore size from 0.2 microns to 200 microns and an average high-flow pore size from 100 microns to 2 millimeters (the average high-flow pore size is greater than the average capillary-pore size); and (c) a phase-change heat-transfer material contained within the porous wick.

Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

An aeroseal comprises a substantially straight portion having a first engagement end and a second engagement end opposite the first engagement end. The aeroseal also comprises a first engagement extension extending transversely from the first engagement end of the substantially straight portion and having a distal end. The aeroseal further comprises a second engagement extension extending transversely from the second engagement end of the substantially straight portion and having a distal end. The aeroseal also comprises a substantially curved portion interconnecting the distal end of the first engagement extension and the distal end of the second engagement extension to form an acute angle between the first and second engagement extensions and facing away from the substantially straight portion.

An aeroseal comprises a substantially straight portion having a first engagement end and a second engagement end opposite the first engagement end. The aeroseal also comprises a first engagement extension extending transversely from the first engagement end of the substantially straight portion and having a distal end. The aeroseal further comprises a second engagement extension extending transversely from the second engagement end of the substantially straight portion and having a distal end. The aeroseal also comprises a substantially curved portion interconnecting the distal end of the first engagement extension and the distal end of the second engagement extension to form an acute angle between the first and second engagement extensions and facing away from the substantially straight portion.