Abstract: Thrust reverser actuation mechanisms comprising a pair of nested screwjacks commonly driven by a screwjack drive motor. The inner screwjack translates the blocker doors aft and the outer screwjack deploys the blocker doors into the engine jet stream. The screwjacks have different thread pitches so that the blocker doors are translated aft at a faster rate of speed than they are deployed into the engine jet stream.

Abstract: A fan jet engine mounted below and rearwardly of the wing of an aircraft. There are a pair of mounting arms which are connected to and extend rearwardly from the rear spar of the wing and connect to the fan case and the core engine case. The major portion of the cowling structure is mounted to slideways, so that the cowling structure can be moved rearwardly to expose the engine for service and repair. The thrust reverser is mounted to the rear of the cowling.

Abstract: The invention relates to thrust reversal devices for jet aircraft turboreactors and particularly for a turbo-fan type engine.The casing E surrounding the engine structure D comprises an intermediate section S3 formed by doors P4 pivoting about an axis 17-17' extending along a chord of passage CA so that the rear part of the door is short, which provides considerable clearance for the doors which may open up to 90.degree., as well as an action of flux F1 flowing in the passage promoting opening of the doors. A jack 21 coupled to each of the doors acts between the fixed structure of the casing and the internal part of the door.

Abstract: A guiding system of the movable fairing of a turbojet engine thrust reverser system comprising two guide pieces mounted on an upper frame fixed to a mast and pieces to be guided attached to the movable fairing. The guide pieces are provided with a groove of a circular cross section and the piece to be guided is a cylindrical body having, on a generatrix and in a radial plane, a flange, the end of which has means to fasten it to a fitting on the movable fairing.

Abstract: An integrated power plant installation system for underwing high-bypass mid-length fan air duct core-mounted engines readily permits disconnection of the entire powerplant at the wing thereby virtually eliminating the necessity of disconnecting the engine and complex systems per se from the support strut when engine replacement or removal proves necessary. Excessive congestion within the vicinity of the strut box structure is eliminated by disposing the engine accessories, and auxiliary equipment and system lines, within the lower quadrant of the powerplant assembly in both a laterally and longitudinally distributed array. Potential catastrophic fire hazards within the nacelle are substantially eliminated by routing the fluid lines and electrical conduits axially aft and upwardly around the circumference of the engine within the nozzle section of the powerplant aft of all rotating discs.

Abstract: Device for the detection of the position of the thrust reverser of a turbojet engine and its locking element, which includes an element integral with the moving part of the reverser, which cooperates with a mechanical locking device and a stationary electrical detection device for detecting the position of an element integral with the reverser and its locking device.The locking device, mounted pivotingly on a support element has on one side of a pivoting axle an arm which is connected with a control cylinder and on the other side a strap having an axle which may be engaged by a hook of the element integral with the moving part of the reverser, moving in a rectilinear motion of translation, the locking device carrying another axle parallel to its pivoting axle and upon which a lever is articulated.

Abstract: The present invention relates to a safety device for automatically throttling down the jet engine of an aircraft provided with a thrust reverser, in the event of untimely operation of said reverser, said thrust reverser comprising at least one obstacle actuated by a mechanism to occupy either a retracted position or an opened out position and controlled means for locking said obstacle in its retracted position. According to the invention, this safety device is characterized in that it comprises means for detecting the position of at least one mobile member of said locking means and for controlling the throttling down means when said member tends to move away from its locking position without any order to open out having been given by the pilot of the aircraft.

Abstract: The invention relates to a thrust reverser for the jet engine of an aircraft. According to the invention, the unlocking of the doors with a view to passage from their folded position to their extended position, is effective only after they have been previously brought into a super-retracted position with respect to the folded position and said reverser comprises stops which allow the doors to pass from the folded position to the super-retracted position only when the rpm of said engine is lower than a threshold close to idling rpm. The invention is particularly applicable to ensuring operational safety of thrust reversers.

Abstract: The engine is of the type having a central body surrounded by a casing defining therebetween a duct for the passage of the flux. The casing comprises a fixed upstream section extended downstream by means in which are housed jacks; a downstream section movable axially to which are fixed the rods of the jacks; and an intermediate section formed of swinging doors mounted between the beams and hinged thereto by lateral pivots, each door being coupled to the mobile downstream section by means of a hinged link so that the movement of the downstream section causes the doors to swing. This type of reverser is designed more especially for turbo-fan engines having a lateral nacelle configuration in which the whole of the flux flows in the annular duct between the central body and the casing.

Abstract: A method and structure for selectively conducting pressurized gas flow over the upper surface of an airfoil, the airflow being selectively directable either rearward through a spanwise outlet to produce thrust and augment lift or, alternatively, directed forward to spoil the aerodynamic flow over the wing to diminish lift and provide a reverse-thrust braking. The structure includes a plenum defined in the airfoil and ducting to receive pressurized air or gas, the plenum being defined in part by a panel longitudinally pivoted at the central portion thereof to, preferably, change the area of a rearward directed opening while concurrently and proportionally changing in the opposite sense the area of a forward oriented opening to selectively direct the pressurized air or gas rearwardly, forwardly, or in combinations of openings while preferably maintaining a substantially constant opening area.

Abstract: The invention is an integrated hydraulic control circuit for actuating the thrust reversers and variable exhaust nozzle on high performance gas turbine engine powered aircraft. The hydraulic circuits for both systems are integrated into a single housing and are served by common elements. The circuit for the deployment and stowage of the thrust reverser buckets is hydraulically sequenced inhibiting the application of hydraulic power to the actuators prior to withdrawal of the locking pin. In a like manner, the thrust reversers must be fully retracted before the locking pin is deployed. The hydraulic circuit for the thrust reversers also includes a pressure compensating circuit which reduces the pressure applied to thrust reverser actuators with the thrust reversers in the stowed position.

Abstract: A lightweight exhaust nozzle/thrust reverser for a gas turbine engine comprises a flap-type exhaust nozzle with a thrust reverser door built into a cutout within each flap. The flaps may be hinged at their forward edges to the engine exhaust duct and may either be actuated or may float freely. Preferably, when the reverser doors are stowed they blend smoothly with the internal and external surfaces of the flaps. Actuation means deploys the doors such that they extend into the gas flow path and coact with each other to form a wall which blocks the axial flow of gas, and they simultaneously open the cutout within which they are disposed and redirect the exhaust gas through the cutouts in an upstream direction. In a preferred embodiment the flaps define the divergent portion of a convergent/divergent exhaust nozzle.

Abstract: Ducted fan propulsion unit for aircraft has a main duct 3 containing a reversible pitch fan 1 rearward of which is provided a flow splitter 13 dividing the main duct into radially outer and inner branch ducts 3A, 3B. A radial passage 15 in the splitter connects the branch ducts and divides the splitter into front and rear parts 13A, 13B. The part of the inner branch duct forward of the radial passage contains an array of stator vanes 12B and has outer and inner wall surfaces 3B1,3B2 both of progressively reducing diameter to urge the flow through that branch duct toward the inlet of a compressor 8 of yet smaller diameter. Stator vanes 12A in the outer branch duct are arranged forward of the radial passage. The arrangement favors a relatively low axial length of the powerplant.

Abstract: A thrust reverser for the gas stream of a fan jet engine. The engine having a surrounding cowl which forms a fan duct therewith that is divided into a forward fixed and an aft translatable section. The thrust reverser mechanism comprises the plurality of blocker doors rotatable in and out of the fan duct. The rotation mechanism of each of the blocker doors comprises a pinion gear rotatable about a central axle which engages the teeth of a pair of opposing gear racks, one gear rack is attached to the forward cowl section and the other is attached to and carried by the aft cowl section and at least one link member pivotably connected at one end to the axle and at the other end to one of the blocker doors. The translation of the aft cowl section causes said blocker doors to rotate in and out of the fan duct and expose and cover gas reversing cascades.

Abstract: Two groups of half shells capable of being retracted from the jet flow, in a position closing the jet pipe. The thrust reverser and the silencer are concentric and their axes of rotation are upstream with respect to their position in the jet flow.

Abstract: 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 air to a wing blowing device to augment wing lift. All of the fan-generated bypass air can be positively forced into the common duct or manifold by operation of a guided flexible metal strip of sufficient length to form a concave helical diverter vane extending for one complete turn in the annular bypass air engine space when activated by a power control mechanism. Fixed coacting guides shape the normally flat metal strip into the proper cross sectional configuration when the strip is driven to its active bypass air diverting position.

Abstract: An improved deployment mechanism for deploying blocker doors between a stowed and a deployed position. At least a pair of operable blocker doors are utilized. These doors are pivotally attached to fixed cowl structure surrounding a turbo fan engine. A yoke member having adjacent curvilinear tracks is carried by a rear translatable cowl section. Sliders are provided that follow the adjacent tracks. A drag link is connected between a slider and fixed aircraft structure and a door deploying link is connected between each blocker door and is associated slider. In a second configuration, more than one blocker door is actuated by a link connected to a single slider, coupled by more than one door deploying link. When the translatable cowl section is translated rearward by conventional actuation, a peripheral outflow passage is formed between the cowl sections and the blocker doors now being deployed redirect the fan air through the peripheral opening.

Abstract: A bypass duct outer cowl includes a fixed cascade disposed between axially spaced fixed cowl portions and a translatable cowl sleeve and blocker doors movably disposed on the respective radially outer and inner sides of the cascade. Actuation and linkage structure located entirely within the outer cowl provides for selectively moving the cowl sleeve rearwardly and rotating the blocker doors to a position across the bypass duct to cause the fan airflow to pass through the cascade in a thrust-reversing manner.

Abstract: There is disclosed a simplified, lightweight, easily stowed thrust control device for the hot core exhaust flow of a jet engine. The device is mounted in the engine strut fairing, downstream of the nozzle exit plane to reduce exposure to the high exhaust temperatures. In a blocking position, the mounting hardware, actuator and actuator linkage is located so as to be cooled by both free stream and fan air, providing a longer operating life, less maintenance and more reliable operation. Simplified construction and mounting arrangement permit the device to be readily retrofitted on existing installations.

Abstract: An aircraft thrust reverser having a plurality of doors rotatably secured to linkage members at each door's center, and rotatably secured to a carriage ring at one end. As the carriage ring moves toward the direction of travel of the aircraft, the linkage members cause the doors to extend in a forward slope, intercepting fan air and directing it outward and forward.

Abstract: A three link system in combination with the linear translation of a rear cowl section for non-linear rotation of each of a plurality of blocker doors for providing constant engine pressure characteristics during all positions of blocker door rotation between stowed and fully deployed. A first link is pivotally attached at one end to the engine and pivotally attached at its other end to a second link member which in turn is pivotally attached at its other end to the blocker door. A third link member is pivotally attached to the engine rearward of the first link connection and pivotally connected at its other end to the second link intermediate the end of the first link and blocker door. Actuators are provided for linear translation of the rear cowl section.

Abstract: The invention relates to a thrust reverser for a jet engine of an aircraft, which comprises two symmetrical doors pivotally mounted about an axis which is transverse and substantially diametrical to the jet of said engine and which is disposed downstream of the jet exhaust pipe thereof, the doors each being pivoted due to two diametrically opposite hinges and occupying a folded or stowed position in which they form part of the fairing of the engine or fuselage of the aircraft, or an unfolded or opened out position in which they are disposed transversely to the jet, while at least one longitudinal jack is provided at the level of a hinge, for the simultaneous control of the doors via connecting rods.

Abstract: A slot seal closure apparatus for use in an aircraft engine mounting strut comprises at least one door which covers a slot formed in the strut to accommodate fore/aft movement of a portion of the engine cowl. When the engine is in a cruise mode, the movable portion of the cowl is in its forwardmost position disengaged from the slot and the door is in a first position covering the slot so as to prevent airflow through the slot. When the engine is placed in a reverse mode, the movable portion of the cowl moves aft and the door swings to a second position spaced from the slot in reaction to the aft movement of the cowl portion so as to expose the slot thereby enabling the movable portion of the cowl to engage the slot.

Abstract: Cascades and associated blocker doors are provided in the lower section of a turbofan engine nacelle such that when the blocker doors are closed the bypass flow is diverted through the open cascades to produce vertical thrust. Vanes are provided in the cascades to assist in directing the diverted airflow in the downward direction. The upper section of the bypass duct is isolated from the lower cascade section by way of horizontal struts extending across the bypass duct. A pair of outer doors may be provided over the cascades such that, when opened, they act to provide side skirts to guide the downward flow of air.

Abstract: Process of landing an airplane on a solid landing surface covered with a layer of water comprising the steps of forming and maintaining a curtain of gas from a point forward and outboard of each of the landing wheels of an airplane on each side of the fuselage thereof to a point forward and central of the wheels and thereby displacing the water of the layer of water from the path of those landing wheels on that solid surface and later releasing the water from the curtain of gas at points lateral of each of the landing wheels while moving the gas curtain and airplane forward at a sufficiently high rate of speed to maintain the landing wheels in contact with the dry surface. Structural modifications of conventional cascade type thrust reversers and target type thrust reversers are provided to accomplish the steps of such process.

Abstract: A thrust reverser for a fan jet engine enclosed by an engine nacelle. The nacelle has a forward section fixed to the aircraft structure and a rearward translatable section attached to the forward section. The nacelle forming a secondary fan nozzle. A pair of blocker doors are pivotally attached to the rearward translatable nacelle section. Drag links are pivotally attached to the forward nacelle section and one of the drag link connects to each blocker door. A cascade ring is fixedly attached to the rear nacelle section and is translatable therewith for positioning within the opening between the nacelle portions when the rearward section is in a translated position. An air motor with drive connections to a plurality of ball-screw actuators provides the means for uniformly translating the rearward section. A recess in the inner surface of the rearward section is provided for the stowing of the links in a position out of the engine gas flow stream when the rearward section is in its stowed forward position.

Abstract: A cascade/clamshell thrust reverser combination for jet engines wherein the clamshell door in the full-forward thrust mode position, covers a cascade arrangement of vane members provided in the annular engine casing. For obtaining the thrust reverser mode, a track and pivot mechanism is employed. Initially, the door moves backwards on the track while simultaneously slightly rotating so that the total movement of the door follows a predetermined arc. During this initial movement the first portion of the vanes are gradually exposed. Upon continuation towards the full reverser mode, the door will move into a rotating movement thereby fully exposing all vanes and closing the forward thrust nozzle opening. The successive combined track/pivot movement to a pivot rotating movement allows for the maneuvering of a maximum large structural sized clamshell door within the multiple contoured confines of the exit casing, thereby providing the most optimum thrust reverser effect.

Abstract: The invention relates to a thrust reverser comprising two symmetrical doors, approximately hemi-truncated in shape, pivotally mounted about an axis which is transverse and substantially diametrical to the jet of a jet engine and which is disposed downstream of the jet exhaust pipe thereof, the doors occupying a folded, or stowed, position in which they determine a sleeve forming part of the fairing of the engine and fuselage of the aircraft, or an unfolded, or opened out, position in which they are disposed transversely with respect to the jet, wherein the structure of each of the doors is such that, in stowed position, the inner volume of the sleeve forms a useful extension of the jet pipe of the engine. The invention finds particular application in the braking of aircraft.

Abstract: The vane structure fits within a side opening of an aircraft jet engine normally covered by a pivoted clam shell arrangement. When the clam shell arrangement is actuated, it swings from the side opening in a direction to intercept thrust gases normally passing rearwardly of the engine and direct the gases laterally out of the side opening, the vane structure directing the gases upwardly and forwardly to provide a reverse thrust. The vane structure itself includes a number of beams lying in parallel vertical planes and a number of vanes in the form of continuous strips extending transversely to the direction of the beams, the beams having slots through which the vanes pass to define an egg crate like interlocked grid structure. The vanes are tilted forwardly slightly relative to the vertical to provide the forward component of gas movement creating the reverse thrust.

Abstract: Thrust reverser for a jet engine of an aircraft, comprising two symmetrical doors mounted to pivot about an axis which is transverse and substantially diametrical with respect to the jet of the engine and which is disposed downstream of the jet exhaust pipe thereof, the doors being adapted to occupy a folded or stowed position in which they form part of the fairing of the engine or fuselage of the aircraft, or an unfolded or opened out position for which they are disposed transversely with respect to the jet. According to the invention, each of the doors is formed by a single skin which is at least substantially hemi-truncated in shape.

Abstract: A relatively simple variable area divergent exhaust nozzle and low drag afterbody integrated with a target-type thrust reverser and used in conjunction with a convergent nozzle for application to the propulsion system of a high performance jet powered aircraft. Two or more aerodynamically shaped afterbody surfaces may be pivoted with a common actuation system to form: first an efficient nozzle-afterbody suitable for subsonic operation; second, a divergent nozzle-afterbody for efficient supersonic operation and; third, a target-type thrust reverser for in-flight or ground roll deceleration.

Abstract: Combination primary and fan air thrust reversal control systems for long duct fan jet engines are disclosed. In one form, the system spoils and expands primary air and, then, allows the spoiled, expanded air to exit from the fan air duct exhaust nozzle while directing fan air in a thrust reversal direction out cascade vanes circumferentially located in the aft portion of the engine nacelle. In other forms, the system directs unequal pressure fan air and primary air through separate thrust reversal ducting and out cascade vanes circumferentially located in the engine nacelle. In equal pressure fan air and primary air systems, the air may be mixed in ducting prior to being emitted from common cascade vanes, or may be maintained separate prior to emission. In still other forms, the primary air is pre-exhausted through separate nozzles located in the primary duct wall, and a portion is then exhausted through the nacelle cascade vanes.

Abstract: An aircraft jet propulsion power plant is fitted with a sliding ejector sleeve for the provision by selection, of an auxiliary flow of ambient air within the sleeve so as to quieten the noise of the gas efflux. The sleeve is mounted independently of the power plant and is supported from a side of the aircraft fuselage. The sleeve mounting structure has an arm which projects into the fuselage to provide a further mounting point, the reaction loads of which act downwardly so as to counteract the downwardly acting weight of the cowl on the side mounting.

Abstract: Gas turbine engine power plants sometimes are provided with thrust reversing equipment, the outlet of which is close to the power plant air intake. Such arrangements create re-ingestion problems. There is described herein an apparatus which either maintains the upstream portion of reversed flow in a given position with respect to the plane of the air intake or alternatively destroys the reversed flow entirely.

Abstract: A gas turbine engine cowl has a portion which translates axially of the remainder, to open or close a reverser gas flow gap. A yoke is attached to the fixed cowl upstream of the gap which yoke is engageable with a member on the translating cowl portion, by dropping thereover as the cowl portion closes the gap. Translation of the cowl portion actuates an abutment via a cam mechanism to release the yoke at such a time as to prevent the yoke dropping too soon, which would result in the cowl portion being unlocked.

Abstract: An exhaust nozzle used in conjunction with an upper surface blown aircraft for directing the exhaust gases from the aircraft engine over the wing and flap surfaces of the aircraft. The nozzle can occupy two positions. The first position, for use in cruise mode, directs the exhaust gases rearwardly in a normal manner. In the second position, used for takeoff and landing, the nozzle outlet area is slightly increased and the nozzle tilted to direct the exhaust gases rearwardly and downwardly across the wing and flap surfaces thereby increasing lift due to the Coanda effect.

Abstract: A thrust reverser arrangement for a fan-type jet propulsion engine comprising a split cowling surrounding the engine and forming a bypass duct with the engine outer wall. The rear portion of the split cowling is translatable rearward for forming a space between the cowling portions. A translatable sleeve having cascades through portions of its walls is interconnected with the rear portion of the cowling and translates therewith and fills the space between the cowling portions. Blocker doors are interconnected to the rear portion and are rotated into the bypass duct during the terminal rearward movement of the rear portion.

Abstract: 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.

Abstract: Production of a downwardly and forwardly directed reverse thrust discharged from a reverse-thrust duct is controlled by a door in the rearward-discharge duct having its rearward portion pivotally mounted for swinging of its forward portion between a position lodged in a recess in the side of the rearward-discharge duct and a position in which the forward edge of the door is spaced from the recess and the door is inclined to deflect jet exhaust from the rearward-discharge duct into the reverse-thrust duct branching from the rearward-discharge duct. The discharge end of the reverse-thrust duct can be closed by a second door and actuating means interconnecting the two doors can move them simultaneously through proportionate degrees of movement.

Abstract: A cascade thrust reverser for a fan-jet engine comprising a two portion shroud surrounding the engine forming a duct therebetween for the rearward directional flow of bypass gases. The forward portion of the shroud is fixed in position. The rear portion of the cowl translatable from a forward reverser stowed position to a rear reverser deployed position. An opening is provided between the two cowl sections for bypass gases to exit the duct when the reverser is deployed. A plurality of pairs of cascade baskets are positioned around the circumference of the cowl intermediate the shroud walls; one of each pair is positioned over the other and nest in a cavity in the forward wall of the rear shroud portion when the reverser is stowed. The innermost cascade baskets pivot into the duct when the reverser is deployed, and direct the bypass gases through the outer cascade baskets for reversing the direction of the flow of bypass gases.

Abstract: A thrust reverser for utilization with wing mounted jet powered aircraft discharging exhaust gases over the wings thereof. The jet engine is housed in a nacelle which is affixed to the forward part of the wing of the aircraft and the nacelle is appropriately contoured for connection to the wing to form part of the aerodynamic profile therewith. A blocker door in stowed condition is contiguous the wing and is similarly profiled. The blocker door is pivotable counterclockwise to a deployed condition wherein it intercepts the airstream before the exhaust gases are discharged through the nozzle. A deflector door is formed in the nacelle in the vicinity of the trailing edge thereof, and it is pivotable clockwise to its deployed condition in which it diverts the gases delivered to it by the blocker door. Separate hydraulic actuators, one associated with the nacelle structure, and one with the wing structure are employed to deploy and stow the blocker and deflector doors.

Abstract: A translating flap convergent/divergent-aircraft engine thrust nozzle and integrated thrust reverser including a cascade for reversing the flow of engine exhaust, an inner exhaust duct-translating segment and an outer cowl normally enclosing the cascade therebetween; a series of blocker doors positioned in a normal stowed, inactive relation in the aft end portion of the thrust nozzle; main, hydraulic actuators are interconnected with and operable to simultaneously translate the translating segment and cowl to open a reverse-exhaust flow path through the cascade; and a cam-operated device interconnected between the translating segment and the blocker doors to automatically reposition the blocker doors to an active position blocking the engine exhaust path through the thrust nozzle in concert with the translation of the translating segment and cowl to their reverse flow-producing positions.

Abstract: Control arrangement including an actuator, such as an air motor, for operating the jet deflector flaps of a thrust reverser, and a pilot valve and a control valve for operating the actuator. The pilot valve controls flow of high pressure air from the jet engine to the control valve. The air flows through a first port in the control valve to the actuator. Air leaving the actuator flows through a second port in the control valve and then back to the pilot valve through which it is exhausted. A pilot valve member initially limits air flow through the second port, but as the flaps are deployed, the second port is gradually opened and the first port gradually closed. The operation is reversed to retract the flaps. The pilot valve may be operated by a switch responsive to contact of the nosewheel of the aircraft with a runway. The pilot and control valve may be included in a single cylindrical body with their valve members rotatable about the axis of the body.

Abstract: A jet engine is conventionally housed in a streamlined nacelle having a rwardly tapering aft-section ending with a trailing edge surrounding the jet propulsion nozzle and presenting ahead of it one or more side outlets for issuing the engine exhaust flow when laterally deflected from said nozzle upon actuation of the thrust-reverser system. This tapering aft-section thus presents a rear annular peripheral zone extending between its side outlets and its trailing edge and having a continuous outer surface subdividable into peripherally alternate segments which lie respectively in longitudinal rearward extension of a side outlet and of an intermediate solid span between consecutive side outlet edges.A controllable nacelle streamlining destroyer is fitted adjacent said solid span in order to project outwardly therefrom into the relative boundary airflow a thin sheet-like obstacle intercepting stream-lines thereof and causing them to separate from the following stretch of the nacelle aft-section outer surface.

Abstract: In an aircraft with a multi-engine configuration at the aft end of the fuselage the engines lie on top and on either side with their air intakes so positioned that downward and sideways noise shielding is provided by the fuselage and the wings, the wings having rearwardly extendible flaps to substantially close at take off and landing, gaps in the noise shield that would otherwise exist between the intakes and the unextended wing trailing edges. The engines exhaust into a noise shielding duct the bottom and side walls of which are provided respectively by a fixed-incidence portion of the tail plane and a pair of fins and rudders upstanding from the tailplane. Upward and downward thrust reversal passages are obtained by rocking back an aft end portion of each engine housing and simultaneously tilting a hingedly mounted forward section of said fixed incidence tail plane portion.

Abstract: A thrust reversal system for a jet aircraft engine, comprising thrust reverser buckets movable between a stowed and a deployed position, an air motor operable under pilot's control to impart movement to the buckets, a piston movable in a cylinder having restricted outlet orifices for automatically decelerating the motor when the buckets approach both the stowed and the deployed position, a locking mechanism for locking the buckets in the stowed position and a flow control valve for controlling the direction of flow of operating air to the motor, the flow control valve, upon selection of deploy, initially occupying a position corresponding to movement of the motor in the direction to stow the buckets and, after release of the locking mechanism, moving to its alternative position to enable the motor to move the buckets to the deployed position.

Abstract: Production of a downwardly and forwardly directed reverse thrust discharged from a reverse-thrust duct is controlled .Iadd.during landing .Iaddend.by a door in the rearward-discharge duct having its rearward portion pivotally mounted for swinging of its forward portion between a position lodged in a recess in the side of the rearward-discharge duct and a position in which the forward edge of the door is spaced from the recess and the door is inclined to deflect jet exhaust from the rearward-discharge duct into the reverse-thrust duct branching from the rearward-discharge duct. The discharge end of the reverse-thrust duct can be closed by a second door and actuating .[.means.]. .Iadd.mechanism .Iaddend.interconnecting the two doors can move them simultaneously through proportionate degrees of movement.