Abstract: A solid rocket motor is described that includes a solid propellant section, a nozzle, and a source of monopropellant, such as liquid monopropellant. The monopropellant is used to control various operational parameters of the solid rocket motor, such as thrust vector control, roll control, extinguishment of the motor, and cooling of the nozzle and/or nozzle throat. The nozzle and the nozzle throat can be an integrated, single piece assembly that facilitates re-use of the nozzle.

Abstract: A multi-pulse rocket propulsion motor for use with vehicles, such as space vehicles like satellites, rockets, and the like. The propulsion motor is a modular system that is capable of providing a plurality of discrete, controllable propulsion pulses. The propulsion motor can be used for primary propulsion of the vehicle and/or as a maneuvering thruster of the vehicle. The propulsion motor includes a plurality of propellant housings each containing a combustible propellant grain, a discharge plenum defining a plenum volume in communication with the discharge of each propellant housing, and a nozzle downstream from and in fluid communication with the plenum volume.

Abstract: A hybrid rocket engine is described that achieves stable, highly efficient hybrid combustion by having a core flow of fuel-rich gas generator gases, with the flow being surrounded with an annular injection of oxidizer. The fuel-rich gas serves to vaporize and decompose the oxidizer, such as nitrous oxide, and prepare it for effective, stable combustion. In one embodiment, this is done at the head-end of a combustion chamber. The combustion products can then be expanded through a nozzle to create thrust. The engine can be an upper stage engine that can include modular thrust chambers and an integrated aerospike nozzle. The thrust chambers can be arranged in an array that rings the top of the aerospike nozzle.

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary sub munitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect.

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary sub munitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect.

Abstract: A hybrid rocket engine is described that achieves stable, highly efficient hybrid combustion by having a core flow of fuel-rich gas generator gases, with the flow being surrounded with an annular injection of oxidizer. The fuel-rich gas serves to vaporize and decompose the oxidizer, such as nitrous oxide, and prepare it for effective, stable combustion. In one embodiment, this is done at the head-end of a combustion chamber. The combustion products can then be expanded through a nozzle to create thrust. The engine can be an upper stage engine that can include modular thrust chambers and an integrated aerospike nozzle. The thrust chambers can be arranged in an array that rings the top of the aerospike nozzle.

Abstract: A high survivability fluid flow sensor includes a sensor housing defining an interior space. A sensor probe has a first end disposed within the interior space. The sensor probe also includes a second end opposite the first end outside the interior space. At least one load cell is disposed within the interior space and is operatively engaged with the first end of the sensor probe. The load cell is configured to detect loading on the sensor probe as a result of fluid flow impinging on the sensor probe adjacent to the second end. The sensor is operable to capture fluid flow data history through an over pressure event via the sensor probe, which exerts pressure upon the piezoelectric load cell(s), thereby enabling analysis of the wave fluid dynamics.

Abstract: A high survivability fluid flow sensor includes a sensor housing defining an interior space. A sensor probe has a first end disposed within the interior space. The sensor probe also includes a second end opposite the first end outside the interior space. At least one load cell is disposed within the interior space and is operatively engaged with the first end of the sensor probe. The load cell is configured to detect loading on the sensor probe as a result of fluid flow impinging on the sensor probe adjacent to the second end. The sensor is operable to capture fluid flow data history through an over pressure event via the sensor probe, which exerts pressure upon the piezoelectric load cell(s), thereby enabling analysis of the wave fluid dynamics.

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary submunitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect. The incendiary portion includes a solid propellant and, optionally, one or more energetic materials selected from the group consisting of phosphorous, boron, magnesium, aluminum, Fluorinert™-aluminum and BKNO3. The incendiary submunition may be in the shape of a ball or a circular disk with a rocket motor therein.

Abstract: An orbital track wind turbine for generation of electrical energy from wind power is provided. The wind turbine includes a plurality of spaced vertical supports to which at least two parallel spaced circular tracks are fixedly secured. These circular tracks are coaxial with one another and are positioned in parallel horizontal planes. A plurality of trucks extend between the circular tracks, the trucks having at least two grooved rollers which partially surround the circular tracks and operate in rolling engagement therewith. A circular power takeoff ring is coaxial with said circular tracks, and the power takeoff ring is attached to the truck which is rotatable in a horizontal plane about its central axis. A plurality of vertical airfoils extends around the circular power takeoff ring, with each of the airfoils being attached to a truck and the power takeoff ring.

Abstract: An orbital track wind turbine for generation of electrical energy from wind power is provided. The wind turbine includes a plurality of spaced vertical supports to which at least two parallel spaced circular tracks are fixedly secured. These circular tracks are coaxial with one another and are positioned in parallel horizontal planes. A plurality of trucks extend between the circular tracks, the trucks having at least two grooved rollers which partially surround the circular tracks and operate in rolling engagement therewith. A circular power takeoff ring is coaxial with said circular tracks, and the power takeoff ring is attached to the truck which is rotatable in a horizontal plane about its central axis. A plurality of vertical airfoils extends around the circular power takeoff ring, with each of the airfoils being attached to a truck and the power takeoff ring.

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary submunitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect. The incendiary portion includes a solid propellant and, optionally, one or more energetic materials selected from the group consisting of phosphorous, boron, magnesium, aluminum, Fluorinert™-aluminum and BKNO3. The incendiary submunition may be in the shape of a ball or a circular disk with a rocket motor therein.

Abstract: A plasma heated arcjet wind tunnel is provided with tunnel segments in the arc-constrictor. The tunnel segments are fabricated of two concentric discs, an outer disc and an inner disc, with a groove formed in an outer edge of the inner disc. The two concentric discs which fit snugly into one another and are joined at their welded interface by a straight and angled butt joint formed between an inner edge of the outer disc and an outer edge of the inner disc. The straight and angled butt joints can be welded by electron beam welding, laser welding, or friction stir welding.