Abstract: An article transport vehicle (200) has: a carrier base (202) configured for movement along a guideway and a pair of gripping arms (216), each gripping arm (216) having a first end (216a) connected to the carrier base (202) and a second end (216b) protruding from the carrier base (202). The pair of gripping arms (216) is movable between a closed position configured for holding an article (302) and an open position configured for releasing the article (302). The article transport vehicle (200) further has a closure mechanism (238) for moving the pair of gripping arms (216) between the closed position and the open position. The closure mechanism (238) is configured for biasing the pair of gripping arms (216) to the closed position and moving the pair of gripping arms (216) to the open position when the carrier base (202) is positioned at a predetermined portion of the guideway.

Abstract: A diagnostic station for inspecting an article transport vehicle movable along a guideway has a diagnostic module associated with the guideway and configured to receive the article transport vehicle when the article transport vehicle is in an inspection position along the guideway. The diagnostic module has at least one of the following: a grip testing substation having at least one force sensor configured for measuring a force exerted by a closure mechanism of the article transport vehicle in a closed position, a pressure testing substation in communication with a source of pressurized air and configured for pressurizing and depressurizing the closure mechanism, and an optical inspection substation having at least one camera configured for capturing image data of the article transport vehicle.

Abstract: The invention could be a stun glove and a method of operating the same, the stun gun could comprise a glove portion made from a laminate of an inside material and an outside material, the laminate forms a cavity adapted for covering at least a portion of a hand within at least a thumb sleeve; an electronic circuitry when activated by a trigger mechanism generates a pulsed electrical charge to a plurality of electrodes, the electronic circuitry being embedded within the laminate in a manner to expose each said electrode to a glove portion exterior; and the trigger mechanism located within the thumb sleeve so as to be proximate to a leading edge of a tip of the thumb sleeve.

Abstract: The invention could be a stun glove and a method of operating the same, the stun gun could comprise a glove portion made from a laminate of an inside material and an outside material, the laminate forms a cavity adapted for covering at least a portion of a hand within at least a thumb sleeve; an electronic circuitry when activated by a trigger mechanism generates a pulsed electrical charge to a plurality of electrodes, the electronic circuitry being embedded within the laminate in a manner to expose each said electrode to a glove portion exterior; and the trigger mechanism located within the thumb sleeve so as to be proximate to a leading edge of a tip of the thumb sleeve.

Abstract: A method of cooling a rocket engine that includes removal of a gaseous propellant from a tank containing liquid propellant, thereby cooling the propellant in the tank, cooling a rocket engine with a coolant, thereby heating the coolant, and transferring heat from the heated coolant into the propellant in the tank, thereby heating the propellant in the tank and maintaining the pressure in the tank. In certain embodiments, the coolant is injected into the rocket engine after transferring heat from the rocket engine to the propellant in the tank.

Abstract: An improved coaxial injector for injecting first and second propellants into a combustion chamber of a rocket engine is provided. The injector includes a first plate, a second plate, a plurality of channels formed in the first plate, and a plurality of tubes extending through the second plate and into the plurality of channels. The tubes inject a first propellant, such as an oxidizer, into the combustion chamber, and the channels inject a second propellant, such as a fuel, around the tubes and into the combustion chamber.

Abstract: A coolant system for a rocket propulsion system having a rocket engine and a propellant tank includes a first heat exchanger that is operatively coupled to the rocket engine. The cooling system also includes a second heat exchanger that is operatively coupled to the propellant tank, a coolant tank that is configured to hold a coolant, and a pump. The cooling system also includes a flow circuit, through which the coolant flows with the aid of the pump. The flow circuit is defined by the pump, the first heat exchanger, the second heat exchanger and the coolant tank. The coolant is pumped by the pump from the coolant tank to the first heat exchanger. The heat of combustion from the rocket engine is transferred to the coolant to cool the rocket engine. The heated coolant transfers the heat therein to the propellant with the second heat exchanger, thereby causing a pressure of the propellant in the propellant tank to be maintained at a desired level.

Abstract: The present invention relates to rocket engine combustion chambers, and more particularly to an improved rocket engine combustion chamber having a jacket. In some embodiments, a combustion system for a rocket engine includes an injector, a cylindrical combustion chamber, and a jacket coupled to the combustion chamber and to the injector. The combustion chamber can expand axially and/or radially with respect to the jacket. The outer surface of the combustion chamber includes a plurality of flow channels. One or more piston seals and/or bellows can be included to allow axial expansion of the combustion chamber with respect to the jacket. A gap formed between the inner surface of the jacket and the outer surface of the combustion chamber allows for radial expansion of the combustion chamber with respect to the jacket.

Abstract: A propulsion system for a rocket engine and a method of cooling a rocket engine includes a propellant tank fluidically coupled to the rocket engine to hold a pressurized propellant, a coolant tank to hold a coolant, a first heat exchanger thermally coupled to the rocket engine and fluidically coupled to the coolant tank, a second heat exchanger thermally coupled to the propellant tank and fluidically coupled to the first heat exchanger, and a third heat exchanger disposed inside the propellant tank to thermally couple a propellant withdrawn from the tank for combustion to a propellant disposed inside the tank. The coolant flows from the coolant tank to the first heat exchanger and through the first heat exchanger to cool the rocket engine. The propellant withdrawn from the propellant tank receives heat from the propellant disposed inside the tank through the third heat exchanger to convert to a gaseous propellant when withdrawn from the propellant tank as a liquid propellant.

Abstract: A propulsion system for a rocket engine and a method of cooling a rocket engine includes a propellant tank fluidically coupled to the rocket engine to hold a pressurized propellant, a coolant tank to hold a coolant, a first heat exchanger thermally coupled to the rocket engine and fluidically coupled to the coolant tank, a second heat exchanger thermally coupled to the propellant tank and fluidically coupled to the first heat exchanger, and a third heat exchanger disposed inside the propellant tank to thermally couple a propellant withdrawn from the tank for combustion to a propellant disposed inside the tank. The coolant flows from the coolant tank to the first heat exchanger and through the first heat exchanger to cool the rocket engine. The propellant withdrawn from the propellant tank receives heat from the propellant disposed inside the tank through the third heat exchanger to convert to a gaseous propellant when withdrawn from the propellant tank as a liquid propellant.

Abstract: A system and method of driving a fuel pump and/or an oxidizer pump in a propulsion system includes pumping an oxidizer from an oxidizer supply to a rocket engine with the oxidizer pump. A first portion of the pumped oxidizer is used for combustion in the rocket engine. The heat from the combustion of the first portion of the oxidizer is then transferred to a second portion of the pumped oxidizer to convert the second portion of the oxidizer to a super-heated gaseous oxidizer. The super-heated gaseous oxidizer operates a motor, which drives the oxidizer pump and/or the fuel pump.

Abstract: An infant simulator (5) is capable of emulating the care requirements of an infant, recording the quality of care, responsiveness of a person caring for the infant simulator (5), and/or signaling the person caring for the infant simulator (5) when care is required. The infant simulator (5) is capable of sensing the unacceptable environmental conditions of abusive impact, abusive compression, improper positioning, exposure to loud noises, over-stimulation, exposure to smoke, exposure to direct sunlight, exposure to temperature extremes to which the infant simulator (5) is subjected, and periodically demanding that the student change the diaper, feed, burp the infant, rest the infant, and rock the infant.