Abstract: Solid rocket motors or ramjets may be provided. Such devices may include a combustion chamber containing at least one fuel, a metal phase alloy film within the combustion chamber, where the metal phase alloy film coupled to the at least one fuel, and an activator operably coupled to the metal phase alloy film, the activator including an electrical activation system, a laser activation system, or an initiator activation system. This allows combined functional features on pulse motors to release inhibitors and ignite solid fuel/propellant. Fast reactions can be achieved by controlling the thickness of the alloys and using multiple layers to achieve the areal energy density. Foils can be rolled and inserted into the fuel/propellant bore. When rolled, it can easily follow the grain bore diameter changes with temperature and provide no additional mechanical loads to the grain.

Abstract: Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is most advantageously employed with conventional AP-containing solid propellant formulations as the main propellant, especially formulations containing both AP, an energetic solid, and a binder. In especially preferred forms, the secondary propellant will include a nitramine which is at least one selected from nitroguanidine (NQ), cyclotrimethylene trinitramine (RDX) and cyclotetramethylenetetranitramine (HMX), and a binder which is at least one selected from HTPB, HTPE or glycidyl azide polymer (GAP). Most preferably, the secondary propellant will include a combination of nitramines which includes NQ and one of RDX or HMX.

Abstract: Solid propellant systems include a main propellant and a secondary propellant in contact with the first propellant that exhibits autoignition temperatures of at least about 100° F. lower than the autoignition temperature of the main propellant. The secondary propellant of the present invention is most advantageously employed with conventional AP-containing solid propellant formulations as the main propellant, especially formulations containing both AP, an energetic solid, and a binder. In especially preferred forms, the secondary propellant will include a nitramine which is at least one selected from nitroguanidine (NQ), cyclotrimethylene trinitramine (RDX) and cyclotetramethylenetetranitramine (HMX), and a binder which is at least one selected from HTPB, HTPE or glycidyl azide polymer (GAP). Most preferably, the secondary propellant will include a combination of nitramines which includes NQ and one of RDX or HMX.

Abstract: A fracturing system for wells has a propellant charge having a known surface area for combustion, and a combustion rate as a function of pressure with lower combustion rates at lower pressures and rapidly increasing combustion rates at higher pressures separated by a knee in the combustion rate function. The propellant charge is initially sealed within a vessel as it is inserted into a well. The system also includes means for creating openings in the vessel on ignition of the propellant charge in the well, such that the openings have a known combined flow area selected to create a condition of choked flow of combustion gases from within the vessel and maintain pressures within the vessel below the knee in the combustion rate function.

Abstract: A multi-pulse rocket is equipped with a thermally insulating barrier that serves as a rupture disk or a movable plug or plate separating staged propellant grains. When a rupture disk it used, the disk can be equipped with a pyrotechnic actuator to weaken the disk upon command, enabling the propellant grain on the fore side of the disk to burst the disk at a relatively low pressure when ignition of the propellant grain is needed for additional thrust. Rupturing of the disk can also be controlled by attitude maneuvering ports on the fore side of the barrier whose open or closed conditions are controlled by independently operable closures. When a movable plug is used, the plug is movable between a closed position separating rocket chamber into subchambers isolating the propellant grains from each other and an open position allowing the flow of combustion gas between the two subchambers to achieve additional axial thrust.

Abstract: A multi-pulse rocket is equipped with a thermally insulating barrier that serves as a rupture disk or a movable plug or plate separating staged propellant grains. When a rupture disk it used, the disk can be equipped with a pyrotechnic actuator to weaken the disk upon command, enabling the propellant grain on the fore side of the disk to burst the disk at a relatively low pressure when ignition of the propellant grain is needed for additional thrust. Rupturing of the disk can also be controlled by attitude maneuvering ports on the fore side of the barrier whose open or closed conditions are controlled by independently operable closures. When a movable plug is used, the plug is movable between a closed position separating rocket chamber into subchambers isolating the propellant grains from each other and an open position allowing the flow of combustion gas between the two subchambers to achieve additional axial thrust.

Abstract: A fracturing system for wells has a propellant charge having a known surface area for combustion, and a combustion rate as a function of pressure with lower combustion rates at lower pressures and rapidly increasing combustion rates at higher pressures separated by a knee in the combustion rate function. The propellant charge is initially sealed within a vessel as it is inserted into a well. The system also includes means for creating openings in the vessel on ignition of the propellant charge in the well, such that the openings have a known combined flow area selected to create a condition of choked flow of combustion gases from within the vessel and maintain pressures within the vessel below the knee in the combustion rate function.

Abstract: A piston tank with elongated contact between the piston and the tank bore to prevent piston cocking and preserve alignment is equipped with a compound piston that includes a carriage (or glider) and a barrier that is movable relative to the carriage. The carriage is an elongate ring with sealing and contact sites between the ring and the tank bore and axially spaced apart, and the barrier moves or changes shape in response to pressure differentials across the barrier imposed by a pressurized driving fluid. The barrier and carriage can thus move between a position allowing the full volume of the tank to be occupied by fuel or other functional fluid and a position ejecting all of the fuel or functional fluid out of the tank through an outlet port. Two examples of the barrier are disclosed—a plate that is movable within the ring and a diaphragm affixed to the ring and deformable in both directions.

Abstract: Control apparatus for a nozzle for a rocket or other vehicle having a combustion chamber with a propellant therein in communication with the nozzle, the nozzle having a throat and a pair of bores extending into the throat The bores may be in opposed or any other suitable relation. A pair of plungers are slidably mounted in the bores and are movable between an open position wherein they are disposed outside of the throat and a closed position wherein they extend into the throat to substantially close it. The plungers have a width or diameter substantially the same as the width or diameter of the throat. Actuator devices are provided for moving the plungers independently of each other to control thrust by controlling the flow of combustion gases through the throat and the pressure in the combustion chamber. The movement of the plungers can also be used for thrust vector control.

Abstract: Control apparatus for a nozzle for a rocket or other vehicle having a combustion chamber with a propellant therein in communication with the nozzle, the nozzle having a throat and a pair of bores extending into the throat The bores may be in opposed or any other suitable relation. A pair of plungers are slidably mounted in the bores and are movable between an open position wherein they are disposed outside of the throat and a closed position wherein they extend into the throat to substantially close it. The plungers have a width or diameter substantially the same as the width or diameter of the throat. Actuator devices are provided for moving the plungers independently of each other to control thrust by controlling the flow of combustion gases through the throat and the pressure in the combustion chamber. The movement of the plungers can also be used for thrust vector control.

Abstract: A cost effective, efficient thermal insulation composition that will have ng shelf life and withstand severe high temperature and pressure conditions in high temperature solid propellant gas generators can be formed of an ethylene propylene, diene monomer (EPDM)/neoprene rubber binders containing silica powder filler and aramid fibers. The specific chemical constituents include EPDM elastomer, 2 Chlorobutadiene 1,3 elastomer, Silica hydrate, Polymerized Trimethyl Dihydroquinoline, Alkylated Diphenylamines and Diphenyl-p-Phenylendiamene, 40% a,a' Bis (Tert-Butylperoxy), Diisopropylbenzene, Napthenic Process Oil, Synthetic Polyterpene Resin, Aramid Fiber (0.25 inch), and Zinc Oxide, Technical.