Did You Know...
...Chester Carlson was a patent agent who tired of having to make multiple copies of patent applications using the only duplication method available at the time: carbon paper. In 1959 he came up with a new copying system and took it to IBM for evaluation. The "experts" at IBM determined potential sales to be only 5,000 units because people wouldn't want to use a bulky machine when they had carbon paper. Carlson's invention was the xerography process, the company founded on the system is Xerox.
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| Number | Title | Issue Date |
| 7340883 | Morphing structure An apparatus is provided that includes a body having a first wall and a second wall, at least one appending structure extending from an end of the body and at least one actuator positioned between the first and second walls. The actuator includes first end coupled t... | 03/11/2008 |
| 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 |
| 7251927 | Jet nozzle mixer A second stage external jet nozzle mixer (20) includes identically formed lobes which equal in number the lobes of the first stage internal mixer. The external mixer works with the internal mixer, and furthers the mixing of the jet engine internal bypass flow... | 08/07/2007 |
| 7229029 | Propulsion system A propulsion system for a jet- or rocket-propelled vehicle in which the resulting jet exhaust nozzle profile is a 3D spiral. The propulsion system can be applied to any jet- or rocket-propelled vehicle, including aircraft and watercraft. The propulsion system also c... | 06/12/2007 |
| 7093423 | Methods and apparatus for operating gas turbine engines A method of assembling a gas turbine engine includes coupling an annular exhaust duct to the gas turbine engine, coupling a plurality of chevrons to the annular exhaust duct, and coupling a chevron actuation system to the annular exhaust duct such that selective ope... | 08/22/2006 |
| 7062901 | Variable geometry nozzle with flexible side wall The disclosed device is directed toward a periodic combustion propulsion system. The periodic combustion propulsion system comprises at least one periodic combustion chamber configured to contain periodic combustion and at least one supersonic exhaust nozzle coupled... | 06/20/2006 |
| 7004802 | Tail cone assembly A tail cone assembly for a watercraft jet pump includes a tail cone body with a shuttle recess, a self-actuated shuttle biased into the shuttle recess, and a pump back pressure inlet orifice through the tail cone body and into the shuttle recess. The shuttle may hav... | 02/28/2006 |
| 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 |
| 6702300 | High temperature seal for large structural movements A high temperature sealing system is operative to seal an interface between adjacent hot structures and to minimize parasitic flow between such structures that move relative to one another in-plane or out-of-plane. The sealing system may be used to seal t... | 03/09/2004 |
| 6102307 | Load strut for a variable geometry nozzle A load strut for divergent master petals of variable geometry nozzles, of the type which exhibit a control system constituted by three ring-like pieces, the external ring piece being divided into two half-rings, which joins the two half-rings and the corr... | 08/15/2000 |
| 6070830 | Faceted exhaust nozzle A fixed geometry duct defining a gas turbine engine exhaust nozzle includes a plurality of circumferentially adjoining flat triangular facets and coaxial first and second openings at opposite ends thereof. A method of making the duct includes scribing a p... | 06/06/2000 |
| 5839663 | Gas turbine exhaust nozzle flap and flap seal apparatus An exhaust nozzle for a gas turbine engine is provided which includes a plurality of flaps and an abradable coating. Each flap includes seal surfaces with depressions disposed therein. The flaps are disposed about a structure within the engine, and are pi... | 11/24/1998 |
| 5788181 | Thermostatic metal actuator for nozzle actuation A nozzle for use on opposing ends of the rotor of a jet powered tri-mode aircraft is disclosed. The nozzle includes two thermally-controlled doors, which are moveable between an open configuration where hot jet engine exhaust is vented therethrough to pro... | 08/04/1998 |
| 5209059 | Active cooling apparatus for afterburners The present invention comprises at least one active cooling apparatus incorporated into the nozzle liner of sidewall of an afterburner. The liner has a plurality of cooling air holes located under the apparatus. Within the liner is a supply of cooling air... | 05/11/1993 |
| 5110050 | Gas turbine engine nozzle A variable geometry nozzle for a gas turbine engine in which a circumferential array of flaps are pivotally connected to the engine by their upstream ends, the flaps comprising interdigitated flexible and rigid flaps. The geometry of the nozzle is varied ... | 05/05/1992 |
| 5044553 | Sidewall deflection control for a two-dimensional nozzle A two-dimensional nozzle is disclosed wherein outward deflection of the sidewalls is controlled by using the load force of the divergent actuators to produce a bending moment within each sidewall which opposes such outward deflection.... | 09/03/1991 |
| 4878617 | Triple axis thrust vectoring exhaust nozzle A variable area, convergent-divergent (10) nozzle for directing the flow of exhaust gas from an aircraft turbine engine to achieve thrust vectoring about yaw, pitch and roll axes includes a convergent section (16) and a divergent section (18) each compris... | 11/07/1989 |
| 4872612 | Rocket motor extendible nozzle exit cone A membrane of refractory material having opposed arcuate edges one of which is longer than the other, having opposed straight edges which when welded together in edge-to-edge relationship form the frustum of cone, is deformed by brake or die press means o... | 10/10/1989 |
| 4850535 | Variably convergent exhaust nozzle for a model ducted fan unit The present invention is a variably convergent exhaust nozzle includes a ring, pluralities of first inner leaves, second inner leaves, lever-arms and hinges and a cable for use with a ducted fan unit and a driving mechanism. The ring has a peripheral edge... | 07/25/1989 |
| 4787559 | Rocket motor extendible nozzle exit cone A rocket motor extendible nozzle is made by folding a sheet stock (metal, etc.) development of a membrane in the form of a cone or conical frustum (with a straight meridian) in such manner that the aft or larger diameter region of the membrane that is con... | 11/29/1988 |
| 4754926 | Rocket motor extendible nozzle exit cone A rocket motor extendible nozzle, in a first embodiment of the invention, is made by folding a sheet stock (metal, etc.) development of a membrane in the form of a cone or conical frustum (with a straight meridian) in such manner that the aft or larger di... | 07/05/1988 |
| 4707899 | Method of making rocket motor extendible nozzle exit cone A rocket motor extendible nozzle, in a first embodiment of the invention, is made by folding a sheet stock (metal, etc.) development of a membrane in the form of a cone or conical frustum (with a straight meridian) in such manner that the aft or larger di... | 11/24/1987 |
| 4666084 | Nozzle assembly A nozzle assembly capable of controlling the hot exhaust gases which flow om the burning solid rocket propellant.... | 05/19/1987 |
| 4649701 | Thrust nozzle with insulation A thrust nozzle of the hollow-cone type affixed to a stationary shell having external insulation on the nozzle and the shell and the nozzle having a liner extending beyond its edge and having insulation over the extended portion.... | 03/17/1987 |
| 4638947 | Pneumatic bag deployment of folded nozzle extensions An apparatus and method for deploying and forming a rocket engine nozzle extension 10. A pneumatic bag 18 within the fixed nozzle 14 of a rocket engine is inflated to push and unfold the nozzle extension 10. The nozzle extension 10 is of the type which at... | 01/27/1987 |
| 4571800 | Method for explosively forming an auxiliary exit cone for the nozzle of a rocket motor A method of and apparatus for forming with a minimum of labor, by explosive forming means, an automatically extendible auxiliary nozzle member or exit cone for a rocket motor, the member having tapered sinusoidal flutes with the stresses and thicknesses t... | 02/25/1986 |
| 4480437 | Unfoldable device for extending the nozzle of a rocket engine The device consists of a frustoconical-shaped skirt formed by a stack of tube rings or coils welded to one another. The tube has a cross-section flattened in the direction of the stack and incorporates on the inside a pyrotechnic device. The pyrotechnic d... | 11/06/1984 |
| 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 |
| 4326686 | Fan jet engine bypass air delivery system for blown wing aircraft lift augmentation device Comparatively cool fan bypass air in the annular space surrounding the air compressor of a fan jet engine is diverted near the front of the engine into a duct leading to right and left hand aircraft wing leading edge ducts which in turn deliver the bypass... | 04/27/1982 |
| 4213566 | Nested cone extendible nozzle system for a rocket motor A nozzle system is provided which comprises a fixed nozzle and a series of movable nozzle cone segments of increasing diameters packaged in a concentric and side-by-side relationship. The movable nozzle cone segments each have aerodynamic drag panels secu... | 07/22/1980 |
| 4184238 | Method of making an extendible/expandable nozzle for rocket engines A skirt-like device attached to the exit end of a rocket engine nozzle is fabricated of thin sheet heat resistant metal; which when extended in operative condition is in frustoconical form, but which prior to engine firing is pleat-folded inwardly into a ... | 01/22/1980 |
| 4180211 | High temperature compressible support and gasket material A high-temperature compressible material especially useful in rocket motors to support nozzle ring inserts, the material including a binder which when pyrolyzed leaves a char having substantial strength, and fillers including carbonaceous fillers such as ... | 12/25/1979 |
| 4125224 | Extendible/expandable nozzle for rocket engines and the like A skirt-like device attached to the exit end of a rocket engine nozzle is fabricated of thin sheet heat resistant metal; which when extended in operative condition is in frusto-conical form, but which prior to engine firing is pleat-folded inwardly into a... | 11/14/1978 |
| 4109460 | Liquid fuel rocket engine having adjustable nozzle throat section A liquid fuel rocket engine comprises a housing having an outer annular wall and an inner annular wall which define therebetween a combustion chamber of substantially uniform cross section and leading to a converging wall section and a nozzle throat of na... | 08/29/1978 |
| 4092010 | Variable fluid passage A device is provided having means for defining a fluid passage which include an inlet section, a throat section, and an outlet section. The fluid passage decreases in size in the inlet section and increases in size in the outlet section. A plurality of fl... | 05/30/1978 |
| 4073257 | Marine propulsion system A jet propulsion system for boats in which the thrust force center line is below the boat reaction center line to urge the propulsion system thrust line to tilt downwardly. The tilting of the propulsion system thrust line downwardly lifts the stern of the... | 02/14/1978 |
| 4026105 | Jet engine thrust reverser A thrust reverser cascade section comprising a plurality of cascade windows mounted in an engine nacelle rearwardly of the fan air compressor, each cascade window including a plurality of cascade elements, is disclosed. The cascade elements are rotatable ... | 05/31/1977 |
| 4005836 | Target thrust reverser A thrust reversal system for an aircraft jet engine comprising a pair of thrust reverser doors constructed of a thin flexible material movable between a stowed and a deployed position and mechanism for moving same.... | 02/01/1977 |
| 3933310 | Rocket nozzle construction and surfaces impervious to hot, high velocity gases A thrust nozzle for a rocket has an improved exit cone made of a strong, refractory material with tufts of high temperature fibers anchored in it to form a pile, in the manner of a carpet. The pile is on the inside of the nozzle, so that propulsive gases ... | 01/20/1976 |
