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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....
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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...
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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,...
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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...
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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...
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H000795 |
Reduced temperature sensitivity launch motor
A rocket motor that has a main exhaust nozzle area and a secondary exhaust ozzle area with the secondary exhaust nozzle area being closed by burst discs that rupture and open secondary nozzle areas...
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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...
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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...
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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...
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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...
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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...
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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,...
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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...
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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...
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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...
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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.
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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...
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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.
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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...
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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...
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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...
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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...
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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...
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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...
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3913666 |
Heat resistant wall construction
A technique of constructing a heat resistive wall with uni-directional quills, such as fibers, wherein a heat resistant surface is formed by the ends of the quills. The structure is formed of a...
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3900675 |
Rocket nozzle comprising pyrolytic graphite-silicon carbide microcomposite inserts
A rigid pyrolytic graphite microcomposite material comprising a matrix of pyrolytic graphite containing embedded therein codeposited crystalline silicon carbide comprising aciculae oriented...
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3897962 |
Gas generator nozzle
A nozzle provided in a gas generator to control gas flow generated by the combustion of a combustible material. The nozzle, disposed in the downstream end of the compartment containing the...
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3802190 |
DEVICE FOR PRODUCING CONTROL MOMENTS IN A ROCKET-PROPELLED MISSILE
A rocket propelled missile includes a housing for a rocket engine having a lurality of control nozzle assemblies arranged around the periphery thereof. Each assembly is continuously supplied with...
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3776466 |
POLYURETHANE FOAM INSERT FOR OVEREXPANDED ROCKET ENGINE NOZZLES TO PREVENT START TRANSIENT SIDELOADS
A polyurethane foam insert is adhesively secured within the nozzle of a regenerative cooled rocket engine. The insert has a central bore which reduces the engine throat to nozzle exit area ratio so...
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3737102 |
CORROSION RESISTANT ROCKET NOZZLE
A corrosion resistant rocket nozzle for small rocket motors is disclosed. The rocket nozzle has a layer of hard anodize coating on the nozzle surface to reduce the effect of erosion during rocket...
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3708036 |
APPARATUS FOR ATTENUATING THE NOISE MADE BY FLUID JETS EJECTED FROM A CONDUIT
An openwork screen is placed in the discharge plane of a conduit discharging a jet of fluid at sonic speeds, to reduce the noise. The screen can be in the form of parallel slats, radial slats or a...
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3700171 |
COOLING TECHNIQUES FOR HIGH TEMPERATURE ENGINES AND OTHER COMPONENTS
Cooling means for a rocket engine nozzle comprising a fusible multi-turn, multi-layer coil of metal surrounding a porous liner in the nozzle and flowing therethrough when melted. Gas bled from the...
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3688988 |
DISPOSABLE ROCKET MOTOR NOZZLE
A disposable rocket motor nozzle that has a converging diverging throat pion with a shaped charge wound about the throat portion to be ignited by conventional igniter means to cause the throat...
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3668872 |
SOLID PROPELLANT ROCKET
A method and apparatus for utilizing the volatility of the combustion products of solid metallic propellants to accelerate metal combustion products to gaseous velocity by recondensing the gaseous...
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3659789 |
THRUST NOZZLE FOR ROCKETS
A fixed, convergent-divergent, rocket nozzle having a movable throat section seated in spherical relationship to adjacent surfaces; so that the rocket may be steered by rotating the throat section.
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3639159 |
STRUCTURAL CARBONACEOUS MATERIALS HAVING IMPROVED SURFACE EROSION CHARACTERISTICS
Structural carbonaceous materials, such as graphite, having improved resistance to oxidation and corrosion at elevated temperatures are obtained by impregnating a solid carbonaceous material with a...
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3635404 |
SPIN STABILIZING ROCKET NOZZLE
A rocket nozzle having a plurality of internal vanes located downstream of he nozzle throat for imparting rotational spin to the rocket about its longitudinal axis. Each vane may have a nonablative...
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3633631 |
ABLATIVE STRUCTURES
Ablative structures are prepared by laying up panels of at least two dissimilar high-temperature resistant materials impregnated with a thermally curable resin so that the panels are at least...
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3599430 |
ABLATIVE INJECTORS
An injector according to the present disclosure comprises an ablative body having an injector face adapted to form a portion of a rocket combustion chamber. A plurality of ports is disposed in the...
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3597821 |
METHOD OF MAKING AN INTEGRATED MATCH MACHINING ROCKET NOZZLE
A rocket nozzle shell-ablative liner composite is disclosed in which a large hot-sized, high-strength unitary nozzle is formed of annularly welded frustoconical ring sections of varying diameters...
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