Abstract: A baffled ram accelerator system includes a ram accelerator tube with an inner surface and an outer surface and a plurality of baffles disposed on the inner surface. The plurality of baffles forms a sequential series of propellant chambers along the longitudinal axis of the ram accelerator tube. An accelerator gun is also disposed on an input end of the ram accelerator tube, and the accelerator gun is positioned to fire a projectile into the ram accelerator tube.

Abstract: The present invention provides a motor including a combustion chamber, an oxidizer injector, a vortex generators and a nozzle. The combustion chamber can be used to dispose a solid fuel, and the oxidizer injector is used to control the flow rate of an oxidizer and to inject the oxidizer into the combustion chamber. The vortex generators is disposed on the inner wall of the combustion chamber for generating eddies to enhance the mixing of the fuel and the oxidizer. Additionally, the nozzle is connected with the combustion chamber for exhausting the gas generated by the combustion of the propellants.

Abstract: An insensitive combined cycle missile propulsion system includes a solid fuel contained within a first section of the missile, a liquid oxidizer contained within a second section of the missile and a solid oxidizer contained within a third section of said missile. A first conduit has a first valve communicating the fuel and the oxidizer and a second conduit, spatially removed from the first conduit, has a second valve communicating the fuel and the oxidizer. An inlet system for delivering atmospheric oxygen for combustion with the fuel rich gases generated within the missile and a nozzle exhausts combustion products that result from combustion of the fuel, the liquid and solid oxidizers, and air.

Abstract: In accordance with a first aspect of the present invention, an aircraft having a scramjet engine is provided. The scramjet engine includes a flowpath which varies in three dimensions. In accordance with a second aspect of the present invention, a method for launching an aircraft having a scramjet engine with a nozzle section and a solid rocket booster positioned within the nozzle section is provided. The method includes the steps of igniting the solid rocket booster to accelerate the aircraft to a speed at which the scramjet engine can operate, clearing the nozzle section by ejecting the solid rocket booster from the nozzle section upon exhaustion of the solid rocket booster; and injecting fuel into a flow of air passing through the scramjet engine and igniting the fuel and the air to provide thrust to the aircraft.

Abstract: Propulsion from combustion of solid propellant pellet-projectiles for providing a useful propulsion that has the advantages of both solid and liquid propulsion engines, and also can make use of either solid chemical propellants or fissionable nuclear material as the fuel. Preferred methods and systems can include a storage chamber for storing solid propellant pellets, a feeding system having a pellet feeding channel and a pellet feeding mechanism connected to the storage chamber and to a gun assembly, which is positioned along a longitudinal axis to eject the pellets at a certain velocity. A triggering system positioned between gun assembly and thrust chamber can initiate the propellant pellet-projectile, and a thrust chamber having a combustion chamber for combustion of propellant pellet-projectile with an exhaust nozzle.

Abstract: A novel combined engine for a single-stage spacecraft is provided that combines a air-breathing engine utilizing oxygen in the atmosphere as oxidizer and rocket engines for obtaining thrust outside the atmosphere and that does not require a portion whose shape is variable in accordance with the flight speed. Rocket engines 15 are provided on struts 12 that form air introduction channels 10 in the air intake section 4. The rocket jets 18 from the rocket engines 15 control the flow of the airflows 16 introduced into the combustion chamber 20 in accordance with the flight speed. When the spacecraft 1 is stationary or in subsonic flight, the rocket jets 18 promote air intake into the combustion chamber 20 by lowering of static pressure due to expansion (ejector effect). In the subsonic flight condition, it performs the role of air compression, mixing with incoming air, fuel injection and ignition and during supersonic/ultra-supersonic flight it performs the role of a variable diffuser.

Abstract: Propulsion from combustion of solid propellant pellet-projectiles for providing a useful propulsion that has the advantages of both solid and liquid propulsion engines, and also can make use of either solid chemical propellants or fissionable nuclear material as the fuel. Preferred methods and systems can include a storage chamber for storing solid propellant pellets, a feeding system having a pellet feeding channel and a pellet feeding mechanism connected to the storage chamber and to a gun assembly, which is positioned along a longitudinal axis to eject the pellets at a certain velocity. A triggering system positioned between gun assembly and thrust chamber can initiate the propellant pellet-projectile, and a thrust chamber having a combustion chamber for combustion of propellant pellet-projectile with an exhaust nozzle.

Abstract: A combined-cycle engine having at least one core engine and at least one ramjet engine. The ramjet utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which the fuel is introduced. The swirl generator effects a toroidal outer recirculation zone and an inner central recirculation zone, both of which are configured in a backward-flowing manner that carries heat and combustion byproducts upstream where they are employed to continuously ignite a combustible fuel/oxidizer mixture in adjacent shear layers, which accelerate flame propagation throughout the core flowfield. The swirl generator provides smooth combustion with no instabilities and minimum total pressure losses and enables significant reductions in the L/D ratio of the combustor.

Abstract: A shut-off system for an orifice of a duct, particularly for an orifice of an air inlet passage that allows air into the combustion chamber of a ramjet, includes a shutter for shutting off the orifice of the duct, and a controllable actuating device capable of acting on the shutter to uncover the orifice. The shutter includes a removable cap which is held on the duct and a locking device which keeps the cap on the duct by at least one locked jaw, which is unlockable. The actuating device includes at least one controllable striker which is capable of unlocking the jaw in such a way as to cause the cap to be ejected from the duct and to uncover the orifice.

Abstract: The present invention relates to a method and device for controlling the solid fuel regression rate of a solid fuel ramjet engine. In a preferred embodiment of the present invention, pressure oscillations are excited using active, closed-loop control to vary the heat transfer, and in turn the regression rate of a solid fuel ramjet engine. The pressure oscillations are excited by introducing small disturbances into the shear layer. The disturbances are amplified in the shear layer and excite pressure oscillations. The disturbances are introduced at a certain phase relative to the pressure oscillations. This is accomplished by closed-loop control. By varying the phase, the amplitude of the pressure oscillations can also be varied, which in turn will vary the heat transfer, regression rate, and thrust level.