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 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 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 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: A solid propellant thrust control system, method, and apparatus for controlling combustion of solid propellants in an opposing grains solid propellant rocket engine (OGRE) is provided. In particular, an opposing grains rocket engine and propulsion system is provided, in which actuator means connected are connected to solid propellant grains disposed in the pressure vessel of the engine. The actuator means are operable to selectively move the solid propellant grains together or apart relative to one another, such that the burning ends of the solid propellant grains decrease or increase relative to one another. This action controls the rate of combustion of the solid propellant grains by varying spacing distance between the burning ends of the solid propellant grains, and enables extinguishment and reignition of the OGRE. Further, a method is providing for controlling the burn rate of solid propellant grains undergoing combustion in an opposing grains rocket engine.

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 solid propellant thrust control system, method, and apparatus for controlling combustion of solid propellants in an opposing grains solid propellant rocket engine (OGRE) is provided. In particular, an opposing grains rocket engine and propulsion system is provided, in which actuator means connected are connected to solid propellant grains disposed in the pressure vessel of the engine. The actuator means are operable to selectively move the solid propellant grains together or apart relative to one another, such that the burning ends of the solid propellant grains decrease or increase relative to one another. This action controls the rate of combustion of the solid propellant grains by varying spacing distance between the burning ends of the solid propellant grains, and enables extinguishment and reignition of the OGRE. Further, a method is providing for controlling the burn rate of solid propellant grains undergoing combustion in an opposing grains rocket engine.

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 and at least one rocket motor that propels the submunition inside of a target volume. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure, 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 oxidizer package for a propellant system for a motor in which the oxidizer is separated from fuel grain, the oxidizer package comprising oxidizer material and an ignition system therefor in a wrapping or sealing material. A hybrid rocket comprising oxidizer material and fuel grain, the oxidizer material being separated from the fuel grain and being in the form of a single package or plurality of packages of oxidizer material and an ignition system therefor, said packages generally conforming to the shape of the rocket. A grid of a pyrotechnic material. A propulsion system for a hybrid rocket comprising oxidizer material in a matrix, mesh, wool, foamed metal or wires of structural or pyrotechnic material.

Abstract: A point-of-sale commercial transaction processing system, particularly suitable for the fast food industry, is provided. The transaction processing system utilizes (1) a customer interaction terminal (CIT) having a video display, an audio speaker, a microphone, and preferably a printer, (2) a computer system in communication with the customer interaction terminal (CIT) and running artificial intelligence routines to process or pre-process verbal requests provided into the microphone of the customer interaction terminal, and (3) a human-controlled response system in communication with the computer system which completes, corrects or verifies requests that cannot be satisfactorily completed by the artificial intelligence routines alone. The human-controlled response system is preferably in communication with the customer interaction terminal (CIT) and the customer via a high speed network connection.

Abstract: A vending machine includes a video camera for transmitting an image of a buyer to a remotely located human operator, a document reader for transmitting an image of identification document(s) to the remotely located human in control of the vending machine, and a user interface which gives the appearance that the machine is autonomous even though the operator's approval is required prior to vending an age-restricted item. The machine also includes a payment acceptor and a dispensing apparatus.

Abstract: Provided is a method for preparing a flowable solid propellant wherein a) liquid oxidizer is added to a tank, b) pellets of cross-linked hydrogel polymer are added to the liquid oxidizer in the tank so that liquid oxidizer is absorbed into the pellets to form flowable combustible pellets and c) the combustible pellets are then flowed into a combustion chamber of a vehicle to combust and the combustion products flow out the propulsion nozzle of the vehicle. Also provided are the liquid oxidizer absorbed flowable combustible pellets so made.

Abstract: A virtual assistant system for information retrieval and management and service request processing includes a user interaction device (UID), a server computer, a system computer, and a human-controlled call center. The UID permits the user to provide voice or written instructions to the system computer via the server computer. The system computer runs artificial intelligence (AI) routines to process or preprocess commands provided into the UID by the user. When possible, the AI routines complete the requested service. Where the AI routines alone are insufficient, a human-controlled call center corrects and completes the service requests. Skilled human labor, then, is only relied upon when needed by the system. A great range of service requests can be made including, e.g.