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| Number | Title | Issue Date |
| 7578452 | Ablative composite assemblies and joining methods thereof A cured ablative composite assembly comprises a housing enclosing a pair of ablative composite sub-assemblies joined by a film adhesive. The cured ablative composite assembly is made by surface treating both ablative composite sub-assemblies in preparation for joini... | 08/25/2009 |
| 7406821 | Adapter device for a rocket engine nozzle having a movable diverging portion An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging portion that is movably mounted relative to a stationary portion of the noz... | 08/05/2008 |
| 7313910 | Jet vane thrust vector control system Disclosed is a jet vane thrust vector control (JV-TVC) system. A general system has many problems in design techniques considering actual operation environments, and does not have reliability in component assembly design. The JV-TVC system improves thrust vector con... | 01/01/2008 |
| 7299636 | Extendible exhaust nozzle bell for a rocket engine An exhaust nozzle bell for a rocket engine including a first part arranged on a motor of the rocket engine, and a second part coupled to the first part. The second part having a stowed position in which the second part surrounds the first part and is positioned clos... | 11/27/2007 |
| 7269951 | Throat retention apparatus for hot gas applications A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein. The flow path has a throat section. The insert is made of material cap... | 09/18/2007 |
| 7251941 | Ablative afterburner An afterburner includes an exhaust duct with a fixed area outer nozzle at an aft end thereof, and an ablative inner nozzle therein. The smaller inner nozzle is consumed during reheat operation to expose the larger outer nozzle for increased propulsion thrust. ... | 08/07/2007 |
| 7051511 | Method and arrangement for preventing encased explosives being caused to explode by an external fire This disclosure relates to a method and an arrangement for preventing explosives such as rocket engines from exploding while subjected to an external fire in an ammunition bunker. The basic principle underlying the invention is that the casing surrounding the explos... | 05/30/2006 |
| 6904755 | Rocket motor nozzle assemblies having vacuum plasma-sprayed refractory metal shell throat inserts, methods of making, and rocket motors including same The rocket motor nozzle assembly of this invention includes a throat insert and a carbon or silica protective eyelid. The throat insert has a carbon throat support and a refractory metal shell. The shell is positioned radially inside the throat support to cover the ... | 06/14/2005 |
| 6901740 | Engine with a central spike for a space launcher The pointed end of a central spike, used in an engine of a space launcher, may have a deformable structure that can adopt either a folded position or a deployed position. ... | 06/07/2005 |
| 6684622 | Rocket exhaust plume signature tailoring Methods and arrangements for tailoring rocket exhaust plume signatures of rocket exhaust systems are disclosed. The tailoring of the rocket exhaust plume signature is accomplished by providing and locating at least one structure having materials and/or ad... | 02/03/2004 |
| 6548794 | Dissolvable thrust vector control vane A dissolvable jet vane (22/30) is a composite structure, having a support frame (38), a plug leading edge (40) connected to the forward edge (42) of the frame (38), and an insulation layer (44) on the side walls of the support frame (38). The dissolvable ... | 04/15/2003 |
| 6510694 | Net molded tantalum carbide rocket nozzle throat A method of making heat engine components, such as rocket nozzle throats, includes forming a body having at least one surface, wherein the body is made of a refractory metal, and compressing a ceramic powder between a die and the at least one surface of t... | 01/28/2003 |
| 6450443 | High torque 2.75-inch rocket nozzle A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible or retractable vanes inside of the nozzle. The vanes are removed from the rocket propelling thrust at rocket exit... | 09/17/2002 |
| 6092621 | Methods and apparatus for suppressing engine test cell howl Methods and apparatus for suppressing cell howl with negligible impact on engine test conditions are described. The apparatus, in an exemplary embodiment includes a flow distorter configured to be positioned close to a nozzle exit of an engine nozzle, and... | 07/25/2000 |
| 5894723 | Rocket engine nozzle with ejectable inserts The diverging part of the nozzle comprises an outer diverging part and at least one inner diverging part of outlet section that is smaller than that of the outer diverging part and designed to be separated therefrom and released at a predetermined instant... | 04/20/1999 |
| 5779151 | Stepped nozzle An insert which allows a supersonic nozzle of a rocket propulsion system to operate at two or more different nozzle area ratios. This provides an improved vehicle flight performance or increased payload. The insert has significant advantages over existing... | 07/14/1998 |
| 5641123 | Expandable nozzle mechanism for a rocket engine A nozzle extension mechanism for a rocket engine is applied to an engine in an upper stage rocket in a multi-stage rocket. Since a high expansion nozzle to be used in the upper stage rocket engine is long, the rocket is divided at a nozzle portion in view... | 06/24/1997 |
| 5598701 | Frangible connection for a thrust reverser for a ducted fan gas turbine A ducted fan gas turbine engine is provided with a thrust reverser which comprises doors which deflect the fan exchaust efflux. Each door is pivotably attached at its downstream end to a common support member by a frangible coupling. In the event of an un... | 02/04/1997 |
| 5490629 | Rocket engine nozzle with an engine diffuser The downstream portion of the diverging part of the nozzle of the rocket engine is extended by an ejectable diffuser which, downstream from the zone where it is connected to the diverging part, presents a zone of smaller cross-section that acts during a f... | 02/13/1996 |
| 5481870 | Rocket engine nozzle with selectively smaller outlet cross-section In a rocket engine nozzle with a selectively smaller outlet cross-section, the nozzle comprising a converging portion which receives the gases produced in a combustion chamber, a nozzle throat of small cross-section and a diverging part connected to the n... | 01/09/1996 |
| 5129604 | Lateral thrust assembly for missiles A lateral thrust assembly for missile maneuvering comprises an annular array of outwardly directed nozzles, each nozzle having a releasable plug normally blocking flow of propellant gases out of the nozzle. A plug release mechanism associated with each pl... | 07/14/1992 |
| 4821962 | Propeller nozzles thereby reducing lateral forces A propeller nozzle, particularly for a missile, comprises a revolution pipe having a forward convergent portion, a minimum section, and a rearward divergent portion with a large outlet throat section. The invention is designed to minimize lateral forces i... | 04/18/1989 |
| 4807531 | Contemporary composite polar boss Composite polar bosses applied in rocket motor cases have very desirable characteristics. The lead time for a boss can be reduced from 6-12 months to 2-3 months. Weight savings for the boss are about 20-40%. A composite polar boss which attaches closures ... | 02/28/1989 |
| 4696431 | Augmentor liner support band having finger positioners An augmentor liner support band is formed having finger positioners for connecting the support band to an augmentor liner; the support band being formed of three built-up ribbons, or strips, or sheet metal, one inner ribbon having spaced fingers extending... | 09/29/1987 |
| 4495763 | Dual-thrust nozzle apparatus for rockets A housing is mounted to the convergent portion of a convergent-divergent thrust nozzle for rockets via legs that space the housing from the nozzle so that it will not obstruct the flow of propulsive gases therethrough. A cavity in the housing holds a seco... | 01/29/1985 |
| 4452395 | Nozzle assembly for a reaction engine A reaction engine, such as a ramjet engine, has a nozzle assembly which maintains acceptable combustion chamber pressures during both high thrust and low thrust modes of flight. To this end, the engine has a primary nozzle in which a swing disc is located... | 06/05/1984 |
| 4434614 | Combustion chamber in a rocket propulsion system with multiple divergent portion The present invention relates to a combustion chamber in a rocket propulsion system comprising a combustion enclosure and a nozzle for ejection of the gases produced in the combustion enclosure, the divergent portion of the nozzle comprises an outer diver... | 03/06/1984 |
| 4426038 | Non-radiating extendible cloth exit cone for rocket nozzles A non-radiating cloth exit cone for a rocket nozzle includes a flared woven refractory cloth structure having the shape of the frustum of a cone with a refractory felt sewn to the exterior surface of the cloth structure for thermal insulation of the cloth... | 01/17/1984 |
| 4384454 | Thrust nozzle for rocket engine with ablating lining A thrust nozzle for a reaction engine having a combustion chamber with a sustained flight discharge nozzle defined therein for the passage of thrust gases and a sustained flight thrust arrangement connected to the combustion chamber for supplying thrust g... | 05/24/1983 |
| 4327886 | Integral rocket ramjet missile A two-stage aerial vehicle which is launched and accelerated by an integral olid booster. After booster burnout and jettison of the booster nozzle, the booster chamber becomes the combustion chamber for a liquid fueled ramjet. The vehicle is designed for u... | 05/04/1982 |
| 4327868 | Swing disc nozzle structure for ramjet engine A ramjet, swing disc, variable nozzle structure with corrosive resistant, coated graphite inserts positioned within oppositely disposed recesses in the swing disc structure.... | 05/04/1982 |
| 4272956 | Time delay device for deployable rocket nozzle skirts A rocket motor expansion cone extension skirt of the combustion gas deployable type is purposely delayed in its deployment by an erodable barrier in the motor's expansion cone upstream of the extension and which diverts combustion gas away from the skirt ... | 06/16/1981 |
| 4242865 | Turbojet afterburner engine with two-position exhaust nozzle A turbojet afterburner engine has an expendable nozzle portion which can be jettisoned when the afterburner is placed in operation.... | 01/06/1981 |
| 4232843 | Molded nozzle for rocket motor A lightweight, relatively inexpensive rocket nozzle assembly which is heat resistant, ablative and electrically insulating. The body of the nozzle is molded in fibre reinforced thermosetting resin integrally with a forward metallic retaining ring, a rear ... | 11/11/1980 |
| 4150540 | Rocket nozzle system An improved rocket nozzle system having a closure insulator located adjacent the combustion chamber of a rocket engine. The closure insulator has formed as an integral part thereof a plurality of nozzles. Each of the nozzles has incorporated therein a thr... | 04/24/1979 |
| 4146180 | Retractable environmental seal A retractable environmental seal for use in sealing the opening of the exit cone for a rocket nozzle comprising a diaphragm-like cover having a central region adapted to be seated in sealing relation with the periphery of the opening and characterized by ... | 03/27/1979 |
| 4109867 | Two-position nozzle A dual-position nozzle having a stationary outer support structure or thr holder and an inner sustain throat assembly which translates during boost-sustain transition is provided. The throat holder includes inner and outer metal support rings joined by t... | 08/29/1978 |
| 4036013 | Noise controllable nozzle closure A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are p... | 07/19/1977 |
| 4033121 | Noise controllable nozzle closure A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are p... | 07/05/1977 |
| 4023356 | Noise controllable nozzle closure A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are p... | 05/17/1977 |
