Abstract: Divergent petal arrangement for convergent-divergent nozzles with thrust vectoring capability through changes in the divergent section geometry, in which the position of each slave divergent petals 4 is determined by a centering mechanism 31, made up by two centering bars 14 and 27 that slide across the sled elements 17 and 18 of the master divergent petals 2, fix a centered axial position between divergent master petals 2 and by a hanger element 13 that collides with the stop elements 25 of the master divergent petals limits the displacement to another axial position, avoiding at the same time and in conjunction with the centering mechanism 31 the displacement of the slave divergent petal 4 away from the master petals 2 when the pressure forces act from the air towards the gas side.

Abstract: A spacecraft attitude and altitude control system utilizes sets of three pulsed plasma thrusters connected to a single controller. The single controller controls the operation of each thruster in the set. The control of a set of three thrusters in the set makes it possible to provide a component of thrust along any one of three desired axes. This configuration reduces the total weight of a spacecraft since only one controller and its associated electronics is required for each set of thrusters rather than a controller for each thruster. The thrusters are positioned about the spacecraft such that the effect of the thrusters is balanced.

Abstract: A translating sleeve structure for a cascade type thrust reverser system for controlling fan air for a turbofan aircraft gas turbine jet engine, such translating sleeve having a plurality of circumferentially arranged spaced blocker doors, each of which is hingedly connected to a door receptacle bonded into a single layer honeycomb panel inner wall of the sleeve at a longitudinal position which is aft of bleed ports positioned in the core cowl of the engine for periodically expelling gases from the engine at elevated temperatures and pressures. Positioning such blocker doors aft of the bleed ports precludes injury to the blocker doors or to their hinged connections to the core cowl and permits smaller uniformly sized doors to be used.

Abstract: The wall downstream of the slot of an ejector forms a divergent angle relative to the upstream wall adjacent to the slot so that the flow discharging from the slot expands and avoids having the primary air from pinching the secondary air and adversely affecting the cooling film issuing from the slot. When multiple slots in the ejector are utilized the downstream wall in relation to the upstream wall is similarly configured to obtain local multi-expansions.

Abstract: A bypass turbo-fan type turbojet-engine having a thrust reverser utilizing pivotally mounted bypass flow deflecting doors, each door having a movable, retractable spoiler at its upstream edge. A control actuator for driving each movable spoiler relative to a door is arranged to cause the spoiler to remain in a stowed retracted position during the initial motion of the door toward its open thrust reversed position and to begin to positively move the spoiler to its extended position into the deflected flow stream as the door nears its fully opened position, the spoiler being fully extended when the door is fully opened at its thrust reversed position.

Abstract: In an aircraft propulsive power unit a thrust reversing arrangement includes a flow redirecting structure having a flow redirecting downstream wall against which gaseous fluid flow in a first flow direction impinges to turn the flow into a second flow direction to produce reverse thrust and an upstream wall round which the fluid flow turns and which has a boundary surface so formed as to support adherence of a boundary layer of the redirected fluid flow at the boundary surface. The upstream wall is provided with projecting elements to generate vortices which prevent or delay separation of the boundary layer from the boundary surface of the upstream wall. Alternatively, the upstream wall is formed with a plurality of flow apertures which are connected by a duct to a pressure differential region or source to cause gaseous fluid to flow through the boundary surface of the upstream wall to prevent or delay separation of the boundary layer.

Abstract: A thrust reverser for aircraft gas-turbine engines includes latch devices that display a tell-tale visible indication when thrust reverser shutters (doors, etc.) are ajar. A latch of the lock at least partly projects from a wall (13, 14) radially bounding the annular structure (12) of the thrust reverser (10) when the latch (37) is in the open mode.

Abstract: A turbojet-engine thrust reverser includes bypass flow deflectors (3) which in a forward thrust mode are retracted into a wall of the primary cowling (4) of the engine and which are driven by linear actuator (6) mounted inside the primary cowling (4) to form an annular flow-deflecting assembly aft of the outlet of the bypass flow duct for producing thrust reversal. Each deflector (3) is independently driven by an actuator (6) and a linkage element (9) into rotation about one or more displaceable pivots (12) which in turn is or are translated by at least one linear actuator along one or more longitudinal guide elements (10). Each actuator (6) is connected to a deflector at the downstream end of the deflector and drives the associated deflector downstream end in an upstream or forward direction, the guide elements extending in a fore and aft direction.

Abstract: A liquid fuel rocket engine wherein the thrust producing exhaust of the engine is directed out of the engine in an annular fashion providing increased thrust and 360 degree thrust vectoring, while presenting the ability to be adaptable to different fuel/oxidizer mixtures, and prevent the sinusoidal shock wave formation typically associated with bell nozzle type rocket engines.

Abstract: An apparatus and method for varying the effective cross sectional area of an opening through a nozzle provides a controller 78 that pulses a fluidic cross flow through an injector associated with the nozzle 68 proximate to the opening of the nozzle. The controller 78 directs the injector 76 to provide a pulsed cross flow having a predetermined frequency, amplitude, or wave form. The pulsed cross flow interacts with a primary flow 14 through the nozzle 68 to partially block the nozzle's opening 72, thereby effectively decreasing the cross sectional area of opening 72 in a jet engine 42. A plurality of pulsed cross flows proximate to a nozzle's throat 70 permits effective afterburner 64 operations even with a fixed geometry nozzle by allowing throttling of the primary flow 14. Further, variations in the cross flow's orientation pulse frequency, amplitude or wave form, or the cross flow's mass flow characteristics can allow vectoring of the primary flow 14.

Abstract: A gas flow guide is disclosed for an aircraft jet engine thrust reverser having a thrust reverser door movably connected to an engine cowling so as to move between forward and reverse thrust positions, the cowling having a reverse thrust opening bounded by a forward edge having a deflector, an opposite lateral side edges, an inner surface of the cowling forming an outer boundary of a gas flow duct, a forward inner surface of the thrust reverser door tapering toward an outer surface so as to form a cavity opening into the gas flow duct when the thrust reverser door is in the forward thrust position, wherein the gas flow guide has at least one guide vane connected to the cowling so as to be located within the cavity when the thrust reverser door is in the forward thrust position and located rearwardly of the deflector extending from the forward edge so as to guide the gas passing through the reverse thrust opening when the thrust reverser door is in the reverse thrust position.

Abstract: A turbojet-engine thrust reverser comprising at least one pivoting hollow door (3) which in the forward-thrust mode is integrated into the external cowling and which in the thrust-reversal mode constitutes a flow-deflecting obstacle by forming a scoop. A movable deflecting cascade (23) comprising vanes is combined with each door (3). The movable cascade (23) hinges about a pivot (24) and comprises at least one upstream portion forming a deflector (26) projecting, in the thrust-reversal mode of the door (3), beyond the outer surface of an outer panel (4) of this door (3) in such manner that any interference between the exhaust flow from the door (3) and the flow deflected to the outside of the door (3) is avoided.

Abstract: An auxiliary inlet (60) for a jet engine has a first rod block (62) attached to a first side (64) of a hole (66) in a skin (68) of an inlet of the jet engine. A second rod block (80) is attached to an opposing side (82) of the hole (66) in the skin (68) of the inlet of the jet engine. A first reinforced elastomer section (70) is attached to the first rod block (62). A center beam (74) has a first side attached to the first reinforced elastomer section (70). A second reinforced elastomer section (78) is attached to the second rod block (80) and attached to the center beam (74). An actuation system (88, 90) is connected to an intake end of the center beam (74). The actuation system (88, 90) moves the center beam (74) from a first in-moldline position to a second out-of-moldline position.

Abstract: A self-closing pivoting door thrust reverser is disclosed in which the linkage interconnecting the thrust reverser door and the thrust reverser panel redirects the forces acting on the thrust reverser door by the thrust reverser panel so as to provide a positive, self-closing force on the thrust reverser door urging it toward, or maintaining it in, the forward thrust position. The door actuator, the thrust reverser door and the thrust reverser panel are all pivotally connected to a link member at three spaced apart pivot points. When in the forward thrust positions, the line of force acting on the thrust reverser door by the thrust reverser panel passes through, or lies radially inwardly of the pivot axis of the thrust reverser door. Thus, the force of pressurized gases acting on the inner surface of the thrust reverser panel will urge the assembly toward its forward thrust position.

Abstract: A thrust reverser for a turbo-fan type turbojet-engine includes hollow, scoop-type pivoting doors (3) which, in the forward-thrust mode, are integrated into the engine and fan cowling and which, in the reversed-thrust mode, constitute scoop type flow deflecting baffles. A movable upstream visor (23), when in the forward-thrust mode, is situated between the upstream edge of the door (3) and the fixed upstream structure (6) covering the downstream structure of the forward frame (8) of the thrust reverser. The control-driven upstream visor (23) pivots about a pivot mounted on the fixed thrust reverser structure and, in the thrust-reversal mode, uncovers the downstream edge of the structure of the forward frame structure (8) and presents an aerodynamic surface to guide the reverse-thrust flow.

Abstract: Axisymmetric nozzles of variable geometry and orientation of flow intended for gas turbine engines, especially for aircraft. The nozzle comprises control means for adjusting the throat area and vectoring the thrust, which means are formed by three rings concentric to the longitudinal axis of the engine, an inner ring, an intermediate ring, and an outer ring, and by a plurality of linear actuators. The outer ring includes two ring segments interarticulated to each other and swingable independently or in unison to vector the thrust of the aircraft, said swinging and corresponding thrust vectoring being limited to a single plane corresponding to the pitch of the aircraft.

Abstract: The invention relates to a bypass turbojet engine having pivoting, hollow thrust reverser doors which, in the forward thrust configuration, are integrated into the external engine cowling and which, in the reverse thrust configuration, constitute scoop baffles that deflect exhaust air flow. A movable deflector baffle cooperates with each door such that, when the door is opened towards a thrust reversing direction, the baffle moves above an outer surface of the outer panel of the door in such a way that undesired interference between the exhaust flow moving through the door and the flow deflected by the outer surface of the door is minimized or avoided.

Abstract: An aircraft gas turbine-engine thrust-reverser specifically designed to withstand impacts possibly caused by objects propelled from the engines around which they are mounted, for instance disk or blade fragments. These impacts have the energy to distort the annular thrust-reverser structure or to break its bracing components. An emergency locking system for such thrust reverser (35) each comprises a hinging latch (38) of which one end is in the form of a hook (40) partly enclosing the lock-interfacing mechanism (43) with the latch (38) being automatically biased into closing by an elastic arrangement (47). Such a configuration allows setting up additional mechanical connections which are able to compensate for any distortion of the thrust-reverser's annular structure or for any ruptured bracing component in the event of impact by an engine piece.

Abstract: A locking system is disclosed for an aircraft jet engine thrust reverser door that is movably connected to an engine cowling so as to be movable between a forward thrust position and a reverse thrust position, the cowling having a reverse thrust opening that is covered by the thrust reverser door when in the forward thrust position and uncovered when the thrust reverser door is in the reverse thrust position. The locking system has a plurality of locking devices attached to the cowling at the forward side of the reverse thrust opening with at least one locking device located on opposite sides of a longitudinal line equidistantly spaced from opposite lateral sides of the thrust reverser door such that the locking devices simultaneously lock the thrust reverser door in the forward thrust position.

Abstract: A gas flow guide is disclosed for an aircraft jet engine thrust reverser having a thrust reverser door movably connected to a cowling so as to move between forward and reverse thrust positions, the cowling having a reverse thrust opening bounded by a forward edge having a deflector, an opposite lateral side edges, an inner surface of the cowling forming an outer boundary of a gas flow duct, a forward inner surface of the thrust reverser door tapering toward an outer surface so as to form a cavity opening into the gas flow duct when the thrust reverser door is in the forward thrust position, wherein the gas flow guide has at least one guide vane connected to the cowling so as to be located within the cavity when the thrust reverser door is in the forward thrust position and located rearwardly of the deflector extending from the forward edge so as to guide the gas passing through the reverse thrust opening when the thrust reverser door is in the reverse thrust position.

Abstract: A thrust reverser comprising a pair of symmetrical thrust reverser doors pivotally mounted on an axis which is substantially diametrically positioned with respect to the exhaust nozzle of an engine, hinge fittings secured to the doors, pivot brackets secured to a fixed part of the engine, pivot bolts securing the hinge fittings of the thrust reverser doors to the pivot brackets and forming the pivot axis for the doors, the pivot brackets having elongated openings formed therein for receiving the pivot bolts, the pivot bolts having elongated shoulders for engaging one of the elongated openings and positioning the pivot bolts therein, and a washer having an elongated boss for engaging another of the elongated openings and thereby positioning the pivot bolt in the elongated openings. A method for carrying out the trimming of the throat area is also disclosed and comprises changing the pivot bolts in order to shift the pivot axis from its original position to a new, offset position.

Abstract: A thrust reverser is disclosed for an aircraft jet engine having a bypass duct enclosing a cowling with an outer cowling surface and a reverse thrust opening extending through the cowling. The thrust reverser has a thrust reverser door in the opening movable between a forward thrust position, in which the thrust reverser door covers the reverse thrust opening, and a reverse thrust position in which the thrust reverser door is moved within the thrust reverser opening, which is then uncovered, into a gas deflecting position at which position a portion of the door extends into the bypass duct. The thrust reverser door has an inner panel defining a part of the gas duct and an outer panel having an outer surface substantially flush with the outer cowling surface when the thrust reverser door is in the forward thrust position. The inner panel is sealed against the cowling.

Abstract: An aircraft thrust reverser mechanism comprises a thrust reverser moveable between a deployed position in which at least a portion of gas flowing through the aircraft engine is redirected in a non-rearward direction and a stowed position in which gas flowing through the engine is not redirected. A thrust reverser lock is provided to prevent inadvertent deployment of the thrust reverser. The thrust reverser lock comprises a locking element rotatable about a pivot between a closed position in which the locking element prevents deployment of the thrust reverser and an open position in which the locking element permits the thrust reverser to be deployed. A retractable blocking element prevents the locking element from moving to the second position unless the blocking element is first withdrawn.

Abstract: A thrust reverser is disclosed for a turbojet engine having a cowling forming an outer boundary of a gas flow duct through which gases flow from a front to a rear, the cowling having at least one reverse thrust opening communicating with the gas flow duct and a thrust reverser door pivotally connected to the cowling so as to move between a forward thrust position wherein the thrust reverser door covers the reverse thrust opening, and a reverse thrust position wherein the reverse thrust opening is uncovered and the thrust reverser door directs at least a portion of the gases flowing through the duct through the reverse thrust opening.

Abstract: A thrust reverser is disclosed for an aircraft jet engine having a cowling with an outer surface and at least one reverse thrust opening, the thrust reverser including a thrust reverser door assembly movable with respect to the cowling between a forward thrust position, in which the reverse thrust opening is uncovered, and a reverse thrust position in which the thrust reverser door uncovers the reverse thrust opening. The thrust reverser door assembly includes an inner structure, an external panel movably connected to the inner structure and one or more resilient devices acting on the inner structure and the external panel to bias the external panel toward the inner structure such that, when the thrust reverser door is in the forward thrust position the external panel is displaced away from the inner structure by contact with the cowling such that an outer surface of the external panel is substantially flush with the outer surface of the cowling.

Abstract: The present invention relates to a thrust reverser for a turbojet engine having a cowling bounding a gas flow duct, the cowling having at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser has a thrust reverser door with forward and rear portions, a first opening in the forward portion, a second opening in the rear portion and a passage communicating with the first and second openings.

Abstract: A thrust reverser is disclosed for a turbofan type turbojet engine assembly with a cowling having an inner cowling surface forming an outer boundary of a gas flow duct, and an outer cowling surface spaced from the inner cowling surface, the inner and outer cowling surfaces joining at a rearmost edge of the cowling, the thrust reverser having a thrust reverser baffle with an outer baffle surface and an inner baffle surface, a forward linkrod pivotally connected to a forward portion of a thrust reverser baffle and to the cowling, and a rear linkrod pivotally connected to the thrust reverser baffle and to the cowling.

Abstract: A thrust reverser is disclosed for a turbojet engine having a cowling with an inner cowling surface forming an outer boundary of a gas flow duct through which gases flow from a front towards a rear portion, the cowling having an outer cowling surface and at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser has a thrust reverser door pivotally connected to the cowling so as to move between a forward thrust position and a reverse thrust position, the thrust reverser door having front and rear edge portions, an outer door surface and an inner door surface with at least one of the outer and inner door surfaces being flush with at least one of the corresponding outer and inner cowling surfaces when the thrust reverser door is in the forward thrust position.

Abstract: An electric control system is disclosed for a turbojet engine thrust reverser having at least one movable component movable between a forward thrust position and a reverse thrust position, the control system having at least one electromechanical drive device mechanically connected to the moveable component such that actuation of the electromechanical drive device moves the component between the forward and reverse thrust positions, and an electronic control unit electrically connected to the electromechanical drive device and to a turbojet engine control system to transmit actuation signals to the electromechanical drive device to control the movement of the component between the forward and reverse thrust positions. The electronic control system preferably also has at least one electrically actuated locking device to hold the movable component in the forward thrust position.

Abstract: A thrust reverser is disclosed for an aircraft turbojet engine having a cowling with an inner surface forming an outer boundary of a gas flow duct, the cowling having at least one reverse thrust opening and a thrust reverser door pivotally attached to the cowling so as to move between a forward thrust position, wherein the thrust reverser door closes the at least one reverse thrust opening and a reverse thrust position, wherein a forward portion of the thrust reverser door moves outwardly from the cowing and a rear portion of the door moves inwardly into the gas flow duct so as to redirect a first portion of the gases flowing through the gas flow duct through the reverse thrust opening.

Abstract: The thrust reverser for a turbo-fan engine is comprised of: a plurality of oors located in openings radially spaced in a shroud enclosing the engine and canalizing the jet flow from the engine, the doors being adapted to be pivoted, within a fixed structure, from a stowed position, in which they do not interfere with the jet flow, to a deployed position in which they block the jet flow and deflect it through the openings; an actuator having a body attached to the fixed structure and a rod attached to the center of each pivoting door for moving the door from the stowed position to the deployed position, and vice versa; and sealing elements comprising a main seal provided on the fixed structure and a separate annular seal located around the actuator body, the sealing elements mating with each door, when in the stowed position, and with the fixed structure to prevent pressure leakage of the jet flow.

Abstract: A pivoting door type thrust reverser assembly for a dual flow engine incls a fixed cowling construction with a front body portion (9) and a rear body portion (12) joined by longitudinal beams (10,11) and defining reversal chambers in each of which a door (7) is pivotably received. The door pivot pins (17) are carried by two pairs of struts (15,16) such that the pivot pins are spaced from the engine axis X-X'.

Abstract: A method and apparatus are provided for inhibiting the formation of inlet vortices in a turbofan engine/nacelle installation 10 for use with an aircraft. The present invention redirects fan air from a fan air bypass duct 16, in a generally downward direction from the outer nacelle 18 in order to generate an air curtain 48 for inhibiting inlet vortex formation.

Abstract: A fail safe emergency lock for a thrust reverser is disclosed in which the thrust reverser is located on a jet engine having a cowling bounding a gas flow duct, the cowling having at least one reverse thrust opening in communication with the gas flow duct. The thrust reverser has a thrust reverser panel movably mounted on the cowling so as to be movable between a forward thrust position, in which the thrust reverser panel covers the reverse thrust opening, and a reverse thrust position in which the reverse thrust opening is uncovered.

Abstract: A thrust reverser is disclosed for a turbojet engine having a cowling forming an outer boundary for a gas flow duct, the cowling having at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser includes a thrust reverser door pivotally attached to the cowling so as to move between a forward thrust position, in which the reverse thrust opening is uncovered and the thrust reverser door covers the reverse thrust opening, and a reverse thrust position in which the thrust reverser door directs at least a portion of the gas flow from the duct through the reverse thrust opening. A panel is incorporated into the thrust reverser such that it is movable between a first position in which an inner surface of the panel forms a portion of the outer boundary of the gas flow duct and a second position wherein the entire panel is located within the gas flow duct.

Abstract: The present invention relates to a thrust reverser for a turbojet engine having a cowling bounding a flow duct through which gases flow from the front of the cowling towards a rear of the cowling, the cowling having at least one reverse thrust opening communicating with the gas flow duct. The thrust reverser has a thrust reverser door pivotally mounted on the cowling so as to be movable between a forward and a thrust position, wherein the thrust reverser door covers the reverse thrust opening, and a reverse thrust position wherein the thrust reverser door uncovers the reverse thrust opening and directs at least a portion of the gases flowing through the gas flow duct outwardly through the reverse thrust opening.

Abstract: A novel pivoting door thrust reverser which provides a nozzle for the exhaust of a bypass engine that ensures a smooth continuous flow path for the exhaust without leakage around the pivoted upper and lower reverser doors. The upper reverser door is provided with a pair of biased cooperating crescent shaped kicker members that are biased outwardly in a controlled movement when the doors are deployed to deflect the upper portion of the reversed exhaust efflux forwardly in a predetermined direction to avoid interference with the control surfaces of the aircraft. The lower reverser door is provided with pivoted splitter plates that are biased outwardly when the door is deployed to abut and form a unitary splitter element that divides the lower exhaust efflux into two portions that are directed forwardly and away from the inlet of the engine to preclude foreign object damage to the engine.

Abstract: A thrust reverser is disclosed for a turbofan jet engine having a fan cowling with an inner surface and a rear edge, and a jet engine cowling having an outer surface spaced from the inner surface of the fan cowling so as to form an annular gas flow duct, the engine cowling extending rearwardly of the rear edge of the fan cowling. A first thrust reverser baffle is located rearwardly of the rear edge of the fan cowling and is pivotally attached to the engine cowling so as to be movable between a forward thrust position, wherein a first surface of the first thrust reverser baffle forms a portion of the outer surface of the engine cowling, and a reverse thrust position in which a first end of the first baffle moves away from the engine cowling such that the first baffle extends into the gas flow from the gas flow duct so as to redirect at least a portion of the gas flow in a reverse thrust direction.

Abstract: In a Hall effect thruster, especially for use in maneuvering satellites, a stream or plume of ions, used to produce the thrust is deflected, by appropriate adjustment of a magnetic field, so as to steer the satellite or other vehicle. The channel, along which the ions are accelerated, is preferably flared outwardly at its open end so as to avoid erosion which would otherwise be caused by the deflection. The adjustment of the magnetic field is preferably achieved by dividing an outer magnetic pole, surrounding the channel, into separate sectors and winding individual electric coils around the sectors. Control of the current through these individual coils is used to make the appropriate adjustments of magnetic field.

Abstract: The invention concerns a thrust reverser for a jet engine, of the type having swing doors (6) pivoting about fixed transverse pivots (7) secured to the rear end of flanges extending in line with pipe of the engine. According to the invention, each door (6) is borne by a connecting piece (10) offset towards the front with respect to a transverse plane passing through the pivot axis and orthogonal to the longitudinal axis of the door. Furthermore, the fairing (4a, 4b) extends as far as the rear end of the flanges, the said fairing and each door (6) being arranged, on the one hand, so as to cover completely the flanges in the folded position of the said door, and, on the other hand, to enable each door (6) to be brought into its deployed position without any interference between the said fairing and door.

Abstract: A thrust reverser for a turbojet engine is disclosed having a first thrust reverser door pivotally attached to the engine cowling so as to be movable between a forward thrust position and a reverse thrust position, the first thrust reverser door having a first inner surface forming a portion of the outer boundary of the gas flow duct when the first thrust reverser door is in the forward thrust position, a first outer surface and a rear portion which extends into the gas flow duct when the first thrust reverser door is in the reverse thrust position so as to direct at least a portion of the gases passing through the duct outwardly through an opening in the cowling, and a second thrust reverser door pivotally connected to the cowling so as to also be movable between a forward thrust position and a reverse thrust position, the second thrust reverser door having a second outer surface which, with the first inner surface of the first thrust reverser door, form opposite boundaries of a passage directing the gases i

Abstract: A thrust reverser is disclosed in which a panel is pivotally attached to the cowling downstream of the movable thrust reverser door and is connected to the door such that movement of the thrust reverser door causes the panel to pivot about its attachment to the cowling. When the door is in its forward thrust position, the inner wall of the door and an inner wall of the panel form a portion of the boundary of the duct through which pass pressurized gases. The pressurized gases exert forces on the inner wall of the door and the inner surface of the panel such that the forces urge the thrust reverser door toward its forward thrust position. Thus, the thrust reverser door is prevented from being inadvertently deployed toward its reverse thrust position even upon failure or malfunction of the door locking or latching mechanisms.

Abstract: A jet vane control system and method for a missile in which the system is compact, rugged, lightweight and detachably connected to the aft end of a missile. The system provides for very quick pitch over and roll control during launch. The system then detaches from the missile so as not to burden the missile during its flight to target. The vanes of the system are divided into quadrants, each having its own, mounting support and gear train assembly. Each vane is also connected through a, detachable coupling to the steering control system of the missile such that actuation of the steering control system simultaneously actuates the jet vane control system.

Abstract: The supersonic ejector utilized for cooling includes a cooling extension axially extending the discharge slot from the throat of the primary stream and is contoured to accelerate primary stream, to direct the primary stream to flow parallel to the secondary stream and match the static pressures of both streams and to ensure that the expansion shocks are upstream of the discharge slot. This supersonic ejector is utilized in one instance for cooling purposes in a two-dimensional vectoring nozzle of a gas turbine engine powering aircraft.

Abstract: A nozzle for a gas turbine engine is provided which includes an outer casing, a convergent section, a divergent section, an external fairing, and apparatus for sealing between the external fairing and the divergent section. The convergent section communicates with the augmentor on one end and with the divergent section on the opposite end. The end of the divergent section opposite that attached to the convergent section is pivotly attached to the external fairing. The divergent section includes a plurality of divergent flaps and divergent flap seals circumferentially spaced. The apparatus for sealing between the external fairing and the divergent section attaches to the divergent flaps and divergent flap seals and mates with the external fairing.

Abstract: A thrust reverser system including a reverse thrust airflow duct (44) extending through an outer structure (46) of an aircraft engine aft nozzle (32) is disclosed. The reverse thrust duct (44) connects a nozzle exhaust duct (34) with the surrounding atmosphere (46). The duct (44) includes an inlet (72) and an outlet (70). A plurality of slats (50) are located within the reverse thrust duct to direct nozzle exhaust (38) from the nozzle exhaust duct (34) in an outward and/or forward direction. One or more outer doors (54) are formed near the outer structure exterior surface (90) for closing off the reverse thrust duct outlet (70) to the atmosphere. One or more inner doors (56) are provided for closing off the duct inlet (72) at the exhaust duct (34). An actuation system moves the inner and outer doors (56), (54) between open and closed positions. In the open position, the inner and outer doors (56), (54) are moved away from the duct (44) to open the airflow duct inlet and outlet.

Abstract: An improved target-type thrust reverser for use with an aircraft jet engine. Jet engines typically are housed in a nacelle and the engine terminates with an exhaust nozzle. The thrust reverser includes an upper door having a shape of a segment of a hollow frusto-conical member with an inner and outer surface, opposed longitudinal edges that taper towards each other, a forward semi-circular edge and a rearward semi-circular edge. The lower door is substantially identical. A pair of linkage arms pivotally support each of the upper and lower doors so that the doors are translatable between stowed and actuated positions. When in the stowed positions, the exterior surface of the doors form a part of the exterior surface of the engine nacelle. When in the actuated position, the doors are positioned rearwardly of the engine exhaust nozzle with their rearward edges in abutment.

Abstract: A gas turbine engine (10) includes a translating sleeve (38) disposed within a downstream portion of an outer nacelle (20). A variable area fan exhaust nozzle (30) is defined between the trailing edge (32) of the translating sleeve (38) and a conical core cowl (26) disposed radially inwardly of the outer nacelle (20) and spaced apart therefrom. The translating sleeve (38) translates downstream to cooperate with the decreasing diameter of the core cowl (26) to increase the area of the fan exhaust nozzle (30).

Abstract: A thrust reverser is disclosed for a turbojet engine having a nacelle with a plurality of beams extending rearwardly from a rear portion of the nacelle on which are pivotally mounted thrust reverser baffles movable between forward thrust positions and reverse thrust positions. The thrust reverser baffles have forward edges, rear edges forming a portion of an exhaust nozzle when the baffles are in their forward thrust positions, outer baffle surfaces substantially flush with the outer surface of the nacelle when the baffles are in their forward thrust positions, and inner baffle surfaces forming a portion of a gas flow duct when the baffles are in their forward thrust positions, such that the exhaust nozzle has a width H measured in a direction parallel to the width of the beam h such that h is equal or greater than 0.6 H.

Abstract: The present invention relates to a thrust reverser for a turbojet engine having at least one thrust reverser door pivotally attached to a cowling so as to pivot about a first pivot axis between a forward thrust position, wherein the thrust reverser door closes a thrust reverse opening in the cowling, and a reverse thrust position in which the thrust reverse opening is opened. The thrust reverser door moves from the forward thrust position to the reverse thrust position about its pivot axis in a first pivot direction. The invention also includes a thrust reverser panel pivotally attached to the cowling so as to pivot about a second pivot axis between a forward thrust position and a reverse thrust position. In pivoting from the forward thrust position to the reverse thrust position, the thrust reverser panel pivots in a second direction about its axis, the pivoting direction of the thrust reverser panel being opposite to the pivoting direction of the thrust reverser door.