Did You Know...
...that Charles Goodyear performed some of his experiments on rubber while in debtor's prison? He was there so often he referred to it as his "hotel". Chronically in debt because of poor business sense and ill health, Goodyear depended on the generosity of friends and family. Even after he unlocked the secret to vulcanizing rubber, he was unable to improve his financial situation. When he died, his estate was $200,000 in debt.
PatentStorm News
Make the Most of Our Site
See this month's Top Inventors and Most Cited Patents.
Stay on top of the latest innovations by subscribing to an RSS feed.
Registered users: Manage your profile.
| Number | Title | Issue Date |
| 7331292 | Venting system for explosive warheads An ordnance venting system has one or more adapters that separate the warhead section from other sections of a rocket, or submunition compartments within the warhead itself. The adapters structurally fail at given temperatures and pressures to reduce the danger of e... | 02/19/2008 |
| 7328571 | Semi-axisymmetric scramjet flowpath with conformal nozzle In accordance with a first aspect of the present invention, an aircraft having a scramjet engine is provided. The scramjet engine includes a flowpath which varies in three dimensions. In accordance with a second aspect of the present invention, a method for launchin... | 02/12/2008 |
| 7251925 | Pressure-based fuel metering unit A fuel delivery system for use, for example in a gas turbine engine system, includes a fuel metering unit including a main fuel inlet. The fuel metering unit includes fuel pressure and temperature sensors. A cavitating venturi is in fluid communication with the main... | 08/07/2007 |
| 7168236 | Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which th... | 01/30/2007 |
| 7012233 | Thrust vectoring a flight vehicle during homing using a multi-pulse motor A method and apparatus for thrust vectoring a flight vehicle during homing are disclosed. The flight vehicle includes a body; a plurality of attitude control mechanisms on the body; a multi-pulse motor housed at least partially in the body; and a control unit housed... | 03/14/2006 |
| 6918243 | Bi-propellant injector with flame-holding zone igniter A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-ho... | 07/19/2005 |
| 6915626 | Blanking-plug system for blanking off an orifice of a pipe, particularly for blanking off an orifice of a duct for introducing air into the combustion chamber of a ramjet A blanking-plug system for blanking off an orifice of a pipe, particularly for blanking off an orifice of a duct for introducing air into the combustion chamber of a ramjet. The blanking-plug system (16) comprises at least one blanking plug (15)... | 07/12/2005 |
| 6631610 | Consumable port cover for ducted integral rocket-ramjet engine In an integral rocket-ramjet engine the air intake ports are covered with a port cover made of a laminate of Pd and Al. This port cover is rapidly consumed in the brief period between the end of the rocket mode and commencement of the ramjet mode to allow... | 10/14/2003 |
| 6557339 | Blanking-cap system for an orifice of a conduit, in particular for an orifice of an air-intake duct into the combustion chamber of a ramjet Blanking-cap system for an orifice of a duct, in particular for an orifice of an air-intake duct into the combustion chamber of a ramjet. The blanking-cap system (16) includes a glass blanking cap (15) and a destruction device (17) which comprises a projectile... | 05/06/2003 |
| 6481198 | Multi-stage rocket motor assembly including jettisonable launch motor integrated with flight igniter This multi-stage rocket motor assembly includes, a one main motor subassembly and a launch motor subassembly. The flight igniter of the main motor subassembly is integrated with the launch motor subassembly to permit the flight igniter to be jettisoned es... | 11/19/2002 |
| 6405526 | Solid fuel propulsion system for a ram jet rocket A solid fuel propulsion system for a ran jet rocket having a combustion chamber (B) surrounded by a tubular casing (2) and a gas generator (G) disposed upstream from the combustion chamber (B) and surrounded by a tubular casing (1) for generation of a com... | 06/18/2002 |
| 6293091 | Axisymmetrical annular plug propulsion system for integrated rocket/ramjet or rocket/scramjet The invention is an airframe which includes a vehicle (12) having a solid propellant rocket engine (14) and a ramjet or scramjet engine (16); a thrust plug (18) extending from an end (20) of the vehicle which directs combustion gases (23 and 64) produced ... | 09/25/2001 |
| 6155041 | Hybrid engine capable of employing at least a ramjet mode and a super ramjet mode The present invention relates to a hybrid engine capable of employing a ramjet mode and a super ramjet mode and comprising a main engine system (3, 4, 5, 8) which burns fuel and which comprises at least one air inlet (3) for an air stream (F), a combustio... | 12/05/2000 |
| 6116019 | Sealing system for an air intake opening of a ram jet combustion chamber The present invention relates to a shut-off system for an orifice for introducing combustion air into a ramjet with a consumable auxiliary motor (14). According to the invention, this shut-off system comprises: an elastic system (28, 29, 31, 32) connected to t... | 09/12/2000 |
| 6058846 | Rocket and ramjet powered hypersonic stealth missile having alterable radar cross section A missile adapted for flight at hypersonic velocities includes an engine operable in rocket and ramjet modes of operation, the engine having an inlet opening, a fuel combustion chamber in the engine housing a boost fuel and a cruise fuel, an axially movab... | 05/09/2000 |
| 5873240 | Pulsed detonation rocket engine A pulse detonation rocket engine, having at least two detonation chambers. The rocket propelled vehicle includes at least one fuel delivery system in fluid communication with each of the at least two detonation chambers, and at least one oxidant delivery ... | 02/23/1999 |
| 5784877 | Rocket-ramjet engine casing port closure The present invention discloses a composite material closure as a port cover for a rocket-ramjet engine and a method of transitioning between rocket booster operation and ramjet operation. The composite material closure is made to be coextensive with an i... | 07/28/1998 |
| 5070691 | Solid propellant canister loaded multiple pulsed or staged rocket A multi-pulse or multi-stage canister loaded solid propellant rocket motor. The canisters are prepared separately and loaded with solid propellant whereby the scrape rate may be reduced after which they are installed in a monolithic case which affords sti... | 12/10/1991 |
| 5035112 | Non-continuous ignition train A pyrotechnic ignition train for use in dual nozzle rocket-ramjet missiles herein a donor device and a receptor charge in the train allow transfer of a pyrotechnic impulse across an air gap between an outer nozzle and an inner concentric nozzle to allow ig... | 07/30/1991 |
| 4972673 | Solid rocket motor with dual interrupted thrust The invention disclosed is a solid propellant rocket motor, capable of providing two separate propulsive impulses to a missile. The rocket motor is connected at one end to the missile body, the other end including an exhaust nozzle. The rocket motor compr... | 11/27/1990 |
| 4956971 | Solid propellant canister loaded multiple pulsed or staged rocket motor A multi-pulse or multi-stage canister loaded solid propellant rocket motor. The canisters are prepared separately and loaded with solid propellant whereby the scrap rate may be reduced after which they are installed in a monolithic case which affords stif... | 09/18/1990 |
| 4936092 | Propellant grain design A solid propellant rocket motor propellant grain configuration having a center bore of a varying diameter, ballistic slots, a stress/ballistic groove, and a burn inhibitor band for withstanding service motor operating environments and providing the requir... | 06/26/1990 |
| 4891938 | Solid fuel burn enhancer A solid rocket motor grain construction is disclosed for use in a ramjet to improve performance. The solid fuel burn enhancer adds oxidizer for burn rate control. Two constructions are disclosed. The inlaid approach places cores of solid low-oxidizer fuel... | 01/09/1990 |
| 4841724 | Rockets An integrated rocket ramjet in which initial acceleration of the rocket is achieved by a rocket fuel propellant and subsequent flight is sustained by a ramjet engine receiving air via a supersonic diffuser from an inlet disposed at the middle of the rocke... | 06/27/1989 |
| 4807435 | Air-breathing jet engine A rocket engine according to the invention has a body generally extending along an axis and adapted to move through the air in a predetermined axial back-to-front direction. This body is formed with axially spaced front and rear fuel-containing combustion... | 02/28/1989 |
| 4745740 | Velocity controller for ramjet missile and method therefor A velocity controller for a ramjet missile, having a supersonic inlet proximate the peripheral skin thereof for admitting air to a combustion zone of a ramjet engine, is comprised of a variable pitch cover disposed in pivotable engagement within the inlet... | 05/24/1988 |
| 4738099 | Bulkhead rupture disc for solid propellant missiles A missile bulkhead rupture disc assembly for disposition between adjacent solid propellant stages which are ignited in sequential order has a central aperture which receives an igniter for detonating the first stage of propellant. In preferred forms, the ... | 04/19/1988 |
| 4651523 | Integral rocket and ramjet engine An integral rocket and ramjet engine (16) comprises, in flow series, an intake duct (18) for aerodynamically compressing air, a port cover (30), a combustion chamber (20) and a propelling nozzle (22). The port cover (30) in a first position prevents air f... | 03/24/1987 |
| 4631916 | Integral booster/ramjet drive A missile drive is provided comprising a single combustion chamber shared by a first, acceleration stage and a second, ramjet cruising stage, said chamber housing the solid propellant to be consumed during acceleration. At least one air inlet is opened at... | 12/30/1986 |
| 4471229 | Method and apparatus for controlling a turbo-generator set In a power control for a turbo-generator, the acceleration power of the difference between the mechanical power supplied to the turbo-generator set and the power delivered by it is determined and, if the supplied power preponderates, a correction signal d... | 09/11/1984 |
| 4441312 | Combined cycle ramjet engine The metallic wall of the combustion chamber of a combined rocket-ramjet engine is lined with solid ramjet fuel overlaid with rocket fuel. After the consumption of the rocket fuel in the boost portion of the flight the solid ramjet fuel burns and ablates p... | 04/10/1984 |
| 4432202 | Flow-through pyrotechnic delay A pyrotechnic delay system for controlling the time of events from initian of an initial ignition impulse to ignition of a secondary output.... | 02/21/1984 |
| 4391094 | Destructable air inlet cover for rocket engines An improved combination of a cover for closing the air inlet openings into he combustion chamber of a jet rocket engine and strike device for destroying the cover is disclosed. In accordance with the improved arrangement, the cover is composed of a materia... | 07/05/1983 |
| 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 |
| 4381642 | Ramjet engine A ramjet engine for aircraft incorporating means for automatically changing from a subsonic combustion ramjet geometry to a supersonic combustion ramjet geometry. This is accomplished by utilizing solid fuel for the ramjet during the subsonic combustion m... | 05/03/1983 |
| 4368620 | Windmills for ramjet engine A solid fueled ramjet engine comprising solid fuel within a combustion chamber in the form of a hollow cylinder, and a windmill at the entrance to the hollow cylinder for promoting better distribution of the air, better mixing of the air and combustion ga... | 01/18/1983 |
| 4357795 | Multi-burn solid fuel restartable rocket and method of use A multi-burn restartable solid rocket fuel having plural layers, each independently ignitable, including a central core, and at least one outer cylindrical layer separated from the central core by a non-ignitable layer, and the method of utilization there... | 11/09/1982 |
| 4341173 | Hydropulse underwater propulsion system A propulsion motor for an underwater vehicle such as an anti-submarine weapon. The motor includes a propulsion chamber into which water is admitted and then rapidly expelled through an exhaust nozzle, developing thrust to propel the vehicle. Gas generator... | 07/27/1982 |
| 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 |
| 4277940 | Integral rocket-ramjet closed loop fuel control system In an integral rocket-ramjet having a combustor which initially serves as a rocket combustion chamber for booster propellant, and after the booster propellant is expended serves as a ramjet combustor where fuel and air are burned, a fuel control system is... | 07/14/1981 |
