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 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 to the stagnation point. In addition, a nose cover is positioned at least partially over or within the at least one fluid passageway and is formed from a material that ablates or melts when the leading edge is exposed to a predetermined critical temperature, the nose cover being configured for restricting the flow of coolant until the nose cover is ablated or melted away.

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 to the stagnation point. In addition, a nose cover is positioned at least partially over or within the at least one fluid passageway and is formed from a material that ablates or melts when the leading edge is exposed to a predetermined critical temperature, the nose cover being configured for restricting the flow of coolant until the nose cover is ablated or melted away.

An apparatus includes multiple layers of phase-stable material, where adjacent layers of the phase-stable material are separated by multiple spaces. The apparatus also includes liquid phase change material in the spaces between the adjacent layers of the phase-stable material. The liquid phase change material is configured to become gaseous phase change material based on thermal energy absorbed by the liquid phase change material. The apparatus further includes at least one release configured to block passage of the liquid phase change material out of the spaces between the adjacent layers of the phase-stable material. The at least one release is also configured to allow passage of the gaseous phase change material out of the spaces between the adjacent layers of the phase-stable material.

A supersonic aircraft fuselage includes a fuselage body having a first end, a second end, a length extending between the first end and second end, a surface, a first flat plane extending from the first end to a center of the fuselage body along the length on the surface, and a second flat plane extending from the second end to the center of the fuselage body along the length on the surface. The surface includes a curved portion conforming to a Sears-Haack body shape and abutting the first flat plane and second flat plane and extending between the first end and second end. A supersonic aircraft includes a first fuselage, a second fuselage, and a space between the first fuselage and second fuselage. The first fuselage and second fuselage form a Busemann biplane geometry within the space.

A supersonic aircraft fuselage includes a fuselage body having a first end, a second end, a length extending between the first end and second end, a surface, a first flat plane extending from the first end to a center of the fuselage body along the length on the surface, and a second flat plane extending from the second end to the center of the fuselage body along the length on the surface. The surface includes a curved portion conforming to a Sears-Haack body shape and abutting the first flat plane and second flat plane and extending between the first end and second end. A supersonic aircraft includes a first fuselage, a second fuselage, and a space between the first fuselage and second fuselage. The first fuselage and second fuselage form a Busemann biplane geometry within the space.

An aerospace vehicle including: a body, wherein the body is configured to generate heat during operation; a coating disposed over at least a portion of the body, the coating being configured to shift a frequency of at least one wavelength of the heat generated by the body from a first frequency to a second frequency having higher transmissivity relative to a neighboring medium surrounding the body as compared to the first frequency.

An aerospace vehicle including: a body, wherein the body is configured to generate heat during operation; a coating disposed over at least a portion of the body, the coating being configured to shift a frequency of at least one wavelength of the heat generated by the body from a first frequency to a second frequency having higher transmissivity relative to a neighboring medium surrounding the body as compared to the first frequency.

Commercial supersonic aircraft and associated system and methods. A representative real time sonic boom warning system can detect when the trajectory of the commercial supersonic aircraft is likely to cause sonic booms that disturb designated areas (e.g., over land or population centers) and notify the operator accordingly.

Commercial supersonic aircraft and associated system and methods. A representative real time sonic boom warning system can detect when the trajectory of the commercial supersonic aircraft is likely to cause sonic booms that disturb designated areas (e.g., over land or population centers) and notify the operator accordingly.