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| Number | Title | Issue Date |
| 7347146 | Supercavitating projectile with propulsion and ventilation jet A supercavitating projectile is disclosed and includes a combustion chamber, a forward-directed jet nozzle and a comparatively larger gas duct/rear-directed jet nozzle. The combustion chamber is filled with a propellant having a hollowed core. The core serves as a p... | 03/25/2008 |
| 7156024 | Device for warhead charges for cargo ammunition units A warhead charge device (18, 18′, 18″, 18′″) arranged to carry liquid explosive (11), and which device is for use in an ammunition cargo unit such as a missile. The device incorporates at least two confined spaces (2, 6, 9) equipped with... | 01/02/2007 |
| 7051659 | Projectile structure A scramjet has a cowl, a center structure, and a plurality of wide pylons connecting the cowl to the center structure, with scramjet engines positioned between adjacent pylons. Leading surfaces of adjacent pylons converge to one another to provide side wall compress... | 05/30/2006 |
| 6966264 | Rocket motors with insensitive munitions systems and projectiles including same An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive munitions c... | 11/22/2005 |
| 6873945 | Rocket motor propellant temperature simulator The present invention comprises a device which is inert and “thermally-equivalent” to actual ordnance. The device can travel with live ordnance and track the propellant temperatures in order to get a more precise propellant temperature for the ordnance. The devi... | 03/29/2005 |
| 6619029 | Rocket motors with insensitive munitions systems An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive ... | 09/16/2003 |
| 6536350 | Stagnation pressure activated fuel release mechanism for hypersonic projectiles A propulsion-assisted projectile has a body, a cowl forming a combustion section and a nozzle section. The body has a fuel reservoir within a central portion of the body, and a fuel activation system located along the central axis of the body and having a... | 03/25/2003 |
| 6125763 | Integral solid booster and hybrid thrust sustaining system and projectile incorporating the same A rocket according to the invention includes a motor having a fuel chamber and an oxidizer tank, a nose portion provided forward of the motor, and a nozzle surrounded by fins provided aft of the motor. The fuel chamber is provided with a relatively centra... | 10/03/2000 |
| 6094906 | Design for a gun-launched rocket One embodiment of this novel rocket system employs at least one rocket motor closure that includes low and high load capability retainers that, respectively, provide an insensitive munitions system during storage and positive locking of a nozzle assembly ... | 08/01/2000 |
| 5817968 | Gas generation with high pressure sensitivity exponent propellant Gas generator apparatus usable with a ducted rocket propellant having a high exponent burn rate, a burn rate that is burn chamber pressure sensitive to a greater degree than are normally used propellants. The gas generator includes elementary pressure reg... | 10/06/1998 |
| 5792981 | Gun-launched rocket A rocket system employing at least one rocket motor closure that includes low and high load capability retainers that, respectively, provide an insensitive munitions system during storage and positive locking of a nozzle assembly at launch. The rocket mot... | 08/11/1998 |
| 5657948 | Control of a projectile by multi-chamber and single-nozzle impeller The disclosure pertains to a projectile guided by successive lateral gas jets by way of pairs of impellers. The impellers of one pair are fired so as to exert opposite moments of rotation. According to the disclosure, the impellers are brought together in... | 08/19/1997 |
| 5481977 | Work-controlled launching device with accumulator A launching device with a work-controlled gas generator employs a dampening piston in combination with an accumulator volume to provide substantially uniform acceleration of a launching piston.... | 01/09/1996 |
| 5435128 | Pyrotechnically driven nozzle restrictor A pyrotechnically driven device for restricting the area of the nozzle throat in a solid propellant rocket motor is disclosed. In one embodiment, the device includes a piston support mounted to the rocket motor in the exit cone. A restrictor is attached t... | 07/25/1995 |
| 5054712 | Projectile with correctable trajectory A spin-stabilized projectile with a correctable trajectory, wherein the projectile possesses lateral or transverse thrust-propulsion devices which are distributed about the circumference thereof, each incorporating an impulse-generating charge inclusive a... | 10/08/1991 |
| 4982913 | Course correction unit This invention relates to a course correction unit, specifically but not exclusively for use on a spin stabilized guided projectile which can produce high speed instantaneous course correction.... | 01/08/1991 |
| 4803925 | Device for the limitation of gas pressure in a combustion chamber provided inside a projectile A device for the limitation of gas pressure in a projectile having an outer shell by the production of a control stream comprises a combustion chamber disposed inside the projectile; the combustion chamber having a combustion chamber lid; control lines co... | 02/14/1989 |
| 4723736 | Rocket staging system An improved rocket staging system for missiles and the like wherein a carriage borne rocket engine assembly is sequentially employed within separate, generally aligned oxidizer stages which are generally coaxially disposed about the central rocket engine ... | 02/09/1988 |
| 4649826 | Retardation system for air launched flares and submunitions A tandem arrangement of a flare and a booster rocket motor is held together by a hollow coupler having hinged spring-loaded wall segments resembling barrel staves that are released on launch to function as a braking device, similar to a drogue parachute. ... | 03/17/1987 |
| 4502649 | Gun-launched variable thrust ramjet projectile A gun-launched ramjet projectile follows a classical vacuum ballistic trajectory by maintaining a thrust-drag balance. The thrust of the ramjet is varied by an air door which bleeds air from the duct that leads from the supersonic diffuser at the front of... | 03/05/1985 |
| 4428293 | Gun-launched variable thrust ramjet projectile A gun-launched ramjet projectile follows a classical vacuum ballistic trajectory by maintaining a thrust-drag balance. The thrust of the ramjet is varied by an air door which bleeds air from the duct that leads from the supersonic diffuser at the front of... | 01/31/1984 |
| 4132165 | Fuel supply system for a missile or the like A missile is initially propelled through space by the burning of solid fuel in a combustor. The heat produced by the combustion of such fuel is used to vaporize a liquid, the pressurized vapor being used to pump liquid fuel to the combustor after the soli... | 01/02/1979 |
| 4095528 | Vehicle with combined fuel tank/warhead A vehicle driven by a combustible fuel propulsion system, in which the fuel emaining upon arrival at the target is exploded to act as a warhead. The vehicle has a fuel tank incorporated into the structure, which will hold more than enough fuel to complete ... | 06/20/1978 |
| 3999379 | Reduction of depressurization thrust termination jolt Thrust termination of a solid propellant rocket motor is obtained by connecting the nozzle to the combustion chamber pressure vessel by means of explosive and extrusable bolts. When it is desired to obtain thrust termination, the explosive bolts are blown... | 12/28/1976 |
| 3946557 | Rocket motor construction Stresses induced by differential expansion and contraction of the solid propellant grain and the rocket motor case to which it is conventionally bonded are obviated by bonding a special sheath to the propellant grain and attaching it to the rocket motor c... | 03/30/1976 |
