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.

The invention discloses a method and modified aerodynamic apparatuses: fluid pushers-off and fluid motion-sensors, making enable efficient implementation and use of a controllable enhanced jet-effect, either the waving jet-effect, the Coanda jet-effect, the lift-effect, the effect of thrust, the Venturi effect, and/or the de Laval jet-effect, all are controllable using the Peltier effect and/or the Seebeck effect. The modified aerodynamic apparatuses are geometrically shaped and supplied with built-in thermoelectric devices, wherein the presence of the thermoelectric devices provides for new functional properties of the modified aerodynamic apparatuses. The method solves the problem of effective control of the operation of modified aerodynamic apparatuses such as airfoil wings of a flying vehicle, convergent-divergent nozzles, loudspeakers, and detectors of acoustic waves, all of a highly-efficient functionality.

The invention discloses a method and modified aerodynamic apparatuses: fluid pushers-off and fluid motion-sensors, making enable efficient implementation and use of a controllable enhanced jet-effect, either the waving jet-effect, the Coanda jet-effect, the lift-effect, the effect of thrust, the Venturi effect, and/or the de Laval jet-effect, all are controllable using the Peltier effect and/or the Seebeck effect. The modified aerodynamic apparatuses are geometrically shaped and supplied with built-in thermoelectric devices, wherein the presence of the thermoelectric devices provides for new functional properties of the modified aerodynamic apparatuses. The method solves the problem of effective control of the operation of modified aerodynamic apparatuses such as airfoil wings of a flying vehicle, convergent-divergent nozzles, loudspeakers, and detectors of acoustic waves, all of a highly-efficient functionality.

Systems and methods of improving the operation of an aircraft during flight are disclosed. In one embodiment, the method comprises deploying spoilers as the speed of the aircraft approaches the maximum operating Mach number of the aircraft, and keeping the spoilers deployed when the speed of the aircraft is substantially at the maximum operating Mach number.

Systems and methods of improving the operation of an aircraft during flight are disclosed. In one embodiment, the method comprises deploying spoilers as the speed of the aircraft approaches the maximum operating Mach number of the aircraft, and keeping the spoilers deployed when the speed of the aircraft is substantially at the maximum operating Mach number.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

An aircraft includes a wing having a longitudinal centerline axis, a leading edge, a trailing edge aft of the leading edge, a wing thickness, and a wing chord, an engine having a longitudinal axis vertically aligned with the wing chord and parallel to the longitudinal centerline axis, a pylon connecting the wing to the engine, and a fairing received over the pylon. The fairing defines a horizontal plane, a first plane perpendicular to the longitudinal axis, and a second plane perpendicular to the longitudinal axis, the second plane being aft of the first plane, the longitudinal axis defining a reference line when projected onto the horizontal plane. The fairing includes a fairing body defining an aerodynamic surface having an outboard portion and an inboard portion configured such that the first plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a first intersection point. The first intersection point is laterally displaced from the reference line by a first distance. The second plane intersects the horizontal plane and the aerodynamic surface of the inboard portion at a second intersection point. The second intersection point is laterally displaced from the reference line by a second distance. The second distance is greater than the first distance.