Abstract: Methods and apparatus for cooling a surface on a flight vehicle and generating power include advancing the vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A first working fluid circulates through a first fluid loop that heats the first working fluid through a first heat intake thermally coupled to the surface and expands the first working fluid in a first thermal engine to generate a first work output. A second fluid loop has a second working fluid that receives heat from the first working fluid and a second thermal engine to generate a second work output. The first and second work outputs are operably coupled to first and second generators, respectively, to power primary or auxiliary systems on the flight vehicle.

Abstract: An aerodynamic body includes an upper surface and a lower surface. The upper surface includes a first portion of a first axisymmetric body. The lower surface is mated with the upper surface. The lower surface includes a waverider shape. The waverider shape is derived from the shockwave generated by a second axisymmetric body.

Abstract: Methods and apparatus for cooling a surface on a flight vehicle and generating power include advancing the vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A first working fluid circulates through a first fluid loop that heats the first working fluid through a first heat intake thermally coupled to the surface and expands the first working fluid in a first thermal engine to generate a first work output. A second fluid loop has a second working fluid that receives heat from the first working fluid and a second thermal engine to generate a second work output. The first and second work outputs are operably coupled to first and second generators, respectively, to power primary or auxiliary systems on the flight vehicle.

Abstract: Methods and apparatus for power generation and/or thermal management on a high speed flight vehicle include circulating a power generation loop working fluid through a power generation loop, which absorbs heat associated with the flight vehicle. A generator operably coupled to the power generation loop generates electrical power. Additionally, a heat transport loop working fluid may circulate through a heat transport loop to provide thermal management through heat transfer.

Abstract: Systems and methods for expanding an operating speed range of a high speed flight vehicle include providing an engine with an inlet air duct, and positioning a heat exchanger in the inlet air duct to cool at least a portion of duct air flow associated with an engine core. Additionally or alternatively, a nozzle assembly includes a cowl fluidly communicating with the engine and having a cowl internal surface defining a cowl orifice, and a plug defines a primary thrust surface. The plug is supported relative to the cowl so that a portion of the primary thrust surface is disposed within the cowl orifice to define a throat therebetween. An actuator is coupled to at least one of the cowl or the plug, and is configured to generate relative movement between the cowl and the plug, thereby to modify the throat.

Abstract: An aerodynamic body includes an upper surface and a lower surface. The upper surface includes a first portion of a first axisymmetric body. The lower surface is mated with the upper surface. The lower surface includes a waverider shape. The waverider shape is derived from the shockwave generated by a second axisymmetric body.

Abstract: A scramjet includes a converging inlet, a combustor configured to introduce a fuel stream into an air stream in a combustion chamber and to combust the fuel air mixture stream to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream. The combustor includes a fuel injection system including at least one arcjet. A method of creating thrust for an aircraft includes compressing a supersonic incoming air stream in a converging inlet, injecting a fuel stream into the air stream in a combustion chamber to create a fuel air mixture stream, igniting the fuel air mixture stream to create an exhaust stream, and exhausting the exhaust stream from a diverging exit nozzle. The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.

Abstract: A scramjet includes a converging inlet, a combustor configured to introduce a fuel stream into an air stream in a combustion chamber and to combust the fuel air mixture stream to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream. The combustor includes a fuel injection system including at least one arcjet. A method of creating thrust for an aircraft includes compressing a supersonic incoming air stream in a converging inlet, injecting a fuel stream into the air stream in a combustion chamber to create a fuel air mixture stream, igniting the fuel air mixture stream to create an exhaust stream, and exhausting the exhaust stream from a diverging exit nozzle. The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.

Abstract: A multi-body aerospace apparatus includes a first aerospace body, a second aerospace body, and a flow separation member. The second aerospace body is attached adjacent to the first aerospace body with a gap disposed between the first aerospace body and the second aerospace body. The flow separation member is attached to the first aerospace body or to the second aerospace body.

Abstract: A vehicle comprises a first stage supersonic aircraft, and a second stage hypersonic aircraft. The second stage aircraft is in tandem with the first stage aircraft.

Abstract: A vehicle comprises a first stage supersonic aircraft, and a second stage hypersonic aircraft. The second stage aircraft is in tandem with the first stage aircraft.

Abstract: Methods, aircraft, and engine nacelles are disclosed. A wing leading edge of a planform is superimposed on a wing shockwave that extends in a first direction from a shockwave apex toward the wing leading edge. A waverider shape is streamline traced between the wing leading edge and a trailing edge of the planform to form a waverider wing. A position of an engine inlet vertex relative to the waverider wing is identified. An inlet shockwave is projected from the inlet vertex in a second direction generally opposed to the first direction. The inlet shockwave intersects the wing shockwave. An inlet leading edge of an engine inlet includes a lower leading edge including a plurality of points where the inlet shockwave intersects the wing shockwave.

Abstract: A toilet overflow prevention device including an overflow valve assembly, a control valve and a water level sensor. The overflow valve assembly is configured to selectively permit a flow of water through the valve assembly from the tank to the bowl of an associated toilet. The water level sensor is configured to provide a control signal in response to detecting an above-normal water level within the bowl of the toilet. The control valve is configured to actuate the overflow valve assembly in response to a control signal from the water level sensor. Preferably, the overflow valve assembly is separate from the primary flush valve of the toilet and is located between the primary flush valve and the bowl of the toilet.

Abstract: A toilet overflow prevention device including an overflow valve assembly, a control valve and a water level sensor. The overflow valve assembly is configured to selectively permit a flow of water through the valve assembly from the tank to the bowl of an associated toilet. The water level sensor is configured to provide a control signal in response to detecting an above-normal water level within the bowl of the toilet. The control valve is configured to actuate the overflow valve assembly in response to a control signal from the water level sensor. Preferably, the overflow valve assembly is separate from the primary flush valve of the toilet and is located between the primary flush valve and the bowl of the toilet.

Abstract: A hypersonic aircraft producing a shock wave during hypersonic flight. The shape of the shock wave changes depending upon changes in Mach speed and angle of attack, the latter of which can vary significantly with flight dynamic pressure. The aircraft includes a body, a pair of wings coupled to the body (or a wing-body) having leading edges, and a deflectable flap system operably coupled to the hinge line of each of the pair of wings. The flap system is positionable in a plurality of positions relative to the pair of wings so as to achieve a generally optimal position capable of maintaining attachment of the shock wave along the leading edge of the flap system at hypersonic speeds. A controller is further operably coupled to the deflectable flap systems for determining the optimal position and outputting a signal that drives the flap system.

Abstract: A hypersonic aircraft producing a shock wave during hypersonic flight. The shape of the shock wave changes depending upon changes in Mach speed and angle of attack, the latter of which can vary significantly with flight dynamic pressure. The aircraft includes a body, a pair of wings coupled to the body (or a wing-body) having leading edges, and a deflectable flap system operably coupled to the hinge line of each of the pair of wings. The flap system is positionable in a plurality of positions relative to the pair of wings so as to achieve a generally optimal position capable of maintaining attachment of the shock wave along the leading edge of the flap system at hypersonic speeds. A controller is further operably coupled to the deflectable flap systems for determining the optimal position and outputting a signal that drives the flap system.

Abstract: The flight vehicle includes an elongated central body having a central axis defined therein and a circumference. A plurality of elongated portions are positioned about the central body. A plurality of airbreathing engines are axisymetrically positioned about the central axis of the central body and between the respective elongated portions. Each flowpath includes a forebody, an inlet, an isolator duct, a combustor, a nozzle, and a mechanism for injecting fuel into the combustor. The forebody externally compresses the air flow. The inlet is downstream of the forebody to capture air flow. The isolator duct is downstream of the inlet to further reduce velocity of the air flow. The combustor is downstream of the isolator duct and finally, the nozzle is downstream of the combustor. The fuel/air mixture is burned in the combustor and expanded in the nozzle for providing thrust. A control mechanism is positioned about the central body for providing control of the flight vehicle.

Abstract: An air-breathing, propulsion-assisted projectile designed to be rocket or gun launched and capable of accelerating to hypersonic velocities includes a body having an encompassing cowl, an air compression section, an engine assembly located adjacent the air compression section, and a nozzle section located adjacent the engine assembly. The engine assembly includes apparatus for fuel storage and delivery to a combustion region. The rear end portion of the cowl is configured to direct the exiting combusted air-and-fuel mixture over the nozzle section of the body.

Abstract: A gas gun-launched, propulsion-assisted scramjet projectile adapted to be fired from a gun, preferably at velocities greater than Mach 5, includes a body with an external compression section, an internal compression section, a combustion section, a nozzle section, and means for channeling ambient fluid to an engine in one of the sections of the body, the channeling means and the body cooperating with the engine to produce thrust greater than drag when the projectile travels at velocities greater than Mach 5. The projectile further includes a plurality of circumferentially spaced stabilization fins located at the nozzle region of the body and a sabot assembly releasably secured to the rear portion of the body, where the sabot assembly includes a plurality of elements joined together about the body rear portion to form a housing for protecting the body rear portion from explosive gases in the barrel of the gun.