Abstract: The proposal is for a thrust nozzle for aircraft fitted with jet engines especially for lateral thrust vector control, in which the upstream ends of at least two flaps (8, 12) actuated via lever-like adjusters are arranged to pivot simultaneously at different angles of rotation about spindles running across the nozzle axis (20) and between walls (22, 23) running substantially parallel to the nozzle axis of a square nozzle housing in such a way that, with a permanently convergent nozzle contour, a narrowest cross-section is formed between the flaps (8, 12) at the outlet side; one end of each lever-like adjuster (28, 29) is to engage in downstream ends of the flaps, said adjusters being arranged at their movably mutually coupled other ends to travel in a guide path (30) which is curved so as to produce continuously different flap rotation angles; one or more narrowest cross-sections can either be kept continuously constant or change dependently upon the jet deflection angle.

Abstract: A STOL aircraft includes propfan engines which are each connected to a lower surface of one of the wings by a pylon. The propfan engine is located directly below the wing and are each equipped with fans at a rear portion thereof. A slat is connected to a leading edge of the wing and not divided by any object, including the pylon and the propfan engine.

Abstract: The invention concerns nozzle control apparatus for VSTOL aircraft power plant having at least one vectorable thrust nozzles 22. The apparatus comprises oscillating means for oscillating the nozzles about a generally vertical axis (at least) so as to enlarge the area 30 affected by the exhaust gases 25, 26 from the nozzles 22 during hovering and/or landing.In the prior art, the hot jet 26 impinges on a relatively small area 30 of the surface 12 which area rapidly exhibits erosion effects; it has been found that the erosion is generally proportional to the local rate of heating, with a surface time constant of a few seconds. Accordingly, ground/deck erosion is alleviated by spreading out the jets 25, 26 and especially the latter to increase their `footprint`, i.e. if the area 32 of the surface 12 being heated is enlarged.

Abstract: An unmanned aircraft is provided which dual turbo shaft engines diving contra-rotating propellers. A bow plane provides pitch control during normal aircraft cruising. The contra-rotating propellers generate a slipstream for wing and tail sections that permit the aircraft to execute hover without the use of complicated tiltable rotor or jet assemblies.

Abstract: A VTOL aircraft has a first engine nacelle mounted under the wing on one side of the fuselage and houses two of the aircraft engines. The first engine nacelle is mounted in close proximity with the fuselage. A second engine nacelle is mounted under the wing on the opposite side of the fuselage from the first nacelle and houses the remaining two engines. The second engine nacelle is mounted in close proximity with the fuselage. The first and second nacelles are movable from positions parallel to the wing for normal flight to positions perpendicular to the wing for vertical flight. Each of the first and second engine nacelles has inlets and nozzles and each of the first and second nacelles is angled in a manner whereby its nozzles are closer to the fuselage than its inlets. First control vanes extend aft of the nozzles of, and are movable with, the first engine nacelle and second control vanes extend aft of the nozzles of, and are movable with, the second engine nacelle.

Abstract: A VTOL aircraft including a fuselage with four nacelles, three vertical stabilizers and a horizontal stabilizer attached to the fuselage. The fuselage and the nacelles are lifting bodies that are configured to jointly form an aerodynamic lifting body which cooperates with the horizontal stabilizer to provide aerodynamic lift to the aircraft in forward flight. Each nacelle contains two rotary engines directly driving corresponding fans which face each other and operate in counter-rotating directions. Each nacelle also contains a system of vanes located at the rear opening thereof, and actuators for extending and retracting the vanes to deflect the airflow over a predetermined range of angles from the horizontal. Each engine utilizes the dynamic pressure of the air behind the fans to provide a source of air for cooling the rotors and exhaust system.

Abstract: A rigid airship has a carrier frame with trianguar cross-ribs interconnected by longitudinal beams, one connectd to each corner of the triangle. Thus, prism-type frame sections are formed which are stiffened by diagonal tensioning members (D). The prism of each frame section (A) has two lateral sides and a base side. Each of the three sides is stiffened with two diagonal tensioning members. Junctions between neighboring frame sections are formed at the triangle corners. Carrier gas cells, the skin of which forms at least part of the airship skin, are secured in the frame sections. The base of each triangle cross-rib forms the base of the frame. One or more air chambers are formed in the belly of the airship below the base of the frame.

Abstract: An engine end and thrust reversing assembly comprising an annular thrust diverting structure which in the cruise configuration is a rearward extension of a fan duct cowl structure. For thrust reversal, the thrust diverting structure is swung rearwardly and inwardly about an inboard hinge axis to form a laterally and forwardly directed thrust reversing opening. A transversely curved blocking plate is pivotally mounted about a vertical axis to the fan duct structure, and in the cruise configuration it is positioned adjacent to a forward extension of the thrust diverting structure so as to surround a portion of the exhaust passageway. In the thrust reversing position, the blocking plate is swung to a position where it extends across the exhaust passageway defined by the thrust diverting structure.

Abstract: A thrust reverser in a two dimensional jet engine exhaust nozzle employs a plurality of reverser apparati that maintain a constant flow throat area, for example, in the reverse throat mode. A single reverser apparatus includes an actuator that operates through a lever upon linkage and a coupler to drive a set of parallel vanes and at least one independent vane. The parallel vanes are connected by a parallelogram of links to the coupler. The independent vanes move in a manner as defined by a cam having a preselected path therein that causes the independent vanes to move in a desired manner to provide the constant throat area.

Abstract: An improved vertical/short takeoff or landing aircraft (10). The aircraft has a canard wing (14), attached to the forward section of the aircraft body, that has an engine (26) on each side. Each engine drives a pusher propeller (42). Located aft of the canard wing (14) is a primary wing (16) that includes a number of control surfaces and that is rotatably attached to the fuselage (12). The primary wing (16) is rotated downwardly about its chordwise axis when the aircraft takes off or lands vertically. When short takeoffs and landings are required the wing is partially rotated and during conventional flight, the wing is rotated to a position that is approximately parallel to the longitudinal axis of the aircraft (12). The aircraft also has a tail control group that consists of a horizontal stabilizer (22) and elevator (34) to where on each side is attached a vertical stabilizer (22) and rudder (36).

Abstract: An airship is described that shows a central rigid frame, extending the length of the airship, about which are arranged at least three equally spaced gas envelopes containing a lifting gas. Propulsion units are located at each end of the central frame and are controllably moved in different directions to control the airship. Also included on the airship is a hot air envelope above the lifting gas envelopes and provided with pivoting masts to increase and decrease the size of the hot air envelope.

Abstract: A flight system capable of passively stable hover comprises an apparatus defining a vertical axis, and including multiple upright ducts spaced about the axis; fluid momentum generators in the ducts to effect flow of fluid downwardly in the ducts; and fluid flow deflector structure in the path of the downwardly flowing fluid, and angled to deflect the fluid flow away from the axis, in such manner as to provide stability in hover of the apparatus.

Abstract: A thrust deflector system for VSTOL aircraft. The thrust directing system consists of a number of spaced-apart, downwardly facing openings along the bottom of the fuselage. The openings are fluidly connected with the outlet of the aircraft engine so that pressurized gas from the aircraft engine is discharged through the openings and away from the fuselage in discrete spaced-apart jets.

Abstract: An airship having improved controllability which comprises: an axial fluid pathway penetrating through a body of the airship in an axial direction, at least one radial fluid pathway crossing the axial fluid pathway and penetrating through the body in a radial direction, the axial fluid pathway and the radial fluid pathway forming a ventilating-thrusting tube having a rigid framework construction, propulsion means, thrust generating direction of which is adjustable, arranged in a crossing region of the axial fluid pathway and the radial fluid pathway, and a lift balloon arranged beside the ventilating-thrusting tube in such a manner that a gap is formed between the ventilating-thrusting tube and the lift balloon to allow air to flow through. This arrangement lowers a tendency of yawing due to a transverse wind. The airship has a semi-rigid and semi-flexible construction capable of making up for drawbacks of both rigid type and flexible type.

Abstract: A high lift vertical takeoff and landing aircraft has first and second fuselages connected by a central airfoil. Jet engines at the leading edge of the airfoil expel propulsive streams simultaneously over top and bottom surfaces of the foil. Extendable flaps are utilized at a trailing edge of the airfoil with a horizontal control blade being attached to the leading edge of the foil. The control blade is within the jet's propulsive stream to permit proportioning of the stream above and below the airfoil.An extendable augmenter wing is attached between the fuselages aft and above the main airfoil to permit airflow in this region to be directed downwardly, accelerating the flow and providing additional lift.The main airfoil is positioned so that the fuselage walls extend above and below the foil. Lateral flow of the main engine exhaust is restrained by these walls. Above the wing the walls and airfoil create a venturi to speed airflow and decrease pressure.

Abstract: A thrust deflector for use in VSTOL aircraft which has a pressurized gas generator. The thrust deflector consists of a number of adjacent nozzles. Each of the nozzles has a body with a first face and a second face. The nozzles further have an inlet for receiving pressurized gas from the pressurized gas generator and at least one outlet connected to the inlet for discharging pressurized gas from the nozzle. Each of the nozzles is rotatable from a first position in which the outlet directs pressurized gas downwardly, to a second position in which the outlet directs pressurized gas rearwardly. In the first position the first and second faces of the bodies of adjacent nozzles are spaced apart to permit air to flow between the nozzles. In the second position the first and second faces of adjacent nozzles are in contact preventing air passage between adjacent nozzles. The thrust deflector may be mounted in stub wings along either side of the fuselage or in a chordwise arrangement in the main wing of the aircraft.

Abstract: A tilt ramp swept edge nozzle for vectoring exhaust gases from an engine mounted in an aircraft has a pair of flaps pivotally affixed to the aircraft in the area of the output end of the engine tailpipe. The flaps are in spaced relation to each other, aligned with the trailing edge of the airfoil of the aircraft and are movable to positions substantially parallel to each other and to positions substantially non-parallel to each other. An actuating system coupled to the flaps moves same relative to each other thereby to maintain a substantially constant effective throat area in the nozzle and providing an increasing nozzle aspect ratio and variable thrust direction during transition from forward to aft throat position of the nozzle.

Abstract: An aircraft includes a nozzle assembly 18, 20 for exhausting efflux from the powerplant. Each nozzle assembly may be moved from a stowed position in which it is flush with the surrounding surface of the aircraft to an operative position in which it projects therefrom to exhaust efflux.

Abstract: A fluid flow diverter system for use with twin engine vertical take-off aircraft. The diverter sysstem is employed to direct a portion of, or all, the working fluid from the first axial flow compressor (14) of either a by-pass engine, a twin fan engine or a variable cycle engine to either a pair of vectorable front nozzles (36) or to a by-pass duct (34). In the event of one engine failing in flight, an attempt at balancing the remaining thrust for vertical landing is made by ducting all the air normally existing from the operative engine's front nozzle (36) across to the inoperative engine's front nozzle (36).

Abstract: In a jet-propelled aircraft of the type in which the propulsion jets are directed onto a wing so as to achieve an ejector effect, two vertical tail-fin surfaces are provided and extend downwardly beneath the center of gravity of the aircraft to return the aircraft to a correct attitude when it tends to move sideways relative to the direction of flight.

Abstract: A rigid airship is disclosed herein having an annular or toroidal airfoil fuselage in front elevation for housing several elongated gas cells containing a buoyant gas such as helium. The fuselage includes at least two longitudinal and a plurality of transverse structural members for supporting the cells. A covering is provided about the fuselage comprising a multiplicity of fitted panels joined by retainer straps and locking nodes. The fuselage defines a central venturi having an annular intake and a contracted exit through which an elongated tapered tail cone extends in coaxial relationship with the fuselage. Boundary layer control is effected via manifolds associated with the fuselage panels and a variable geometry venturi passageway is effected by longitudinal movement of a control compartment and adjoining tapered tail cone.

Abstract: A thrust vector control for a jet engine is accomplished by controllable flaps which have an inner, jet flow facing contour with a double curvature. One curvature section is convex and extends between the leading edge of the flap and a transition point. The other curvature section is concave and extends between the transition point and the trailing edge of the flap. The flap or flaps are arranged downstream of the propulsion jet nozzle and are tilted into the jet stream as required for the vector control. A pressure sensor is arranged so as to measure or pick-up a pressure value, preferably near the trailing edge of the flap, which pressure value depends on the dynamic pressure head in that area. The respective pressure value is used in a closed loop control circuit for operating the tilting drive of the respective flap.

Abstract: A thrust vectoring structure is provided for VSTOL aircraft having a pressurized gas generator and at least one rearward facing outlet with an opening for discharging pressurized gas from the pressurized gas generator. The thrust vectoring structure has a plurality of horizontal dividers extending between the sides of the opening. A front flap is rotatably mounted adjacent the front edge of the dividers and a rear flap is rotatably mounted adjacent the rear edge of the dividers. The flaps are rotatable from a horizontal position to a vertical position.

Abstract: A lighter-than-air type vehicle comprising a frame-work and a series of inflatable lift bags secured to said framework. The lift bags inwardly contain heating elements and a gas, such as hydrogen or helium, in intimate contact with the heater elements. A source of power is coupled to the heater elements is such that the supply of electrical current, for example, to said elements can be varied as to increase or decrease the degree of inflation of the respective lift bags. Propulsion structure is affixed to the framework and preferably comprises a pair of oppositely revolving propellers which are independently controlled. A shroud and interior plate-like vanes surround the propellers and are constructed and powered to vary the air stream, as to direction, coming from the propeller area.

Abstract: The invention is a short/vertical takeoff and landing aircraft. In detail, it comprises an airframe having aerodynamic lift and flight control surfaces. An engine is mounted in the airframe in a reversed position having the inlet facing toward the rear of the aircraft and the exhaust nozzle assembly, having a pair of exhaust nozzles, facing toward the front. The exhaust nozzles extend outward from the sides of the aircraft and are rotatable from a vertically downward position to provide upward thrust to a horizontally rearward direction to provide forward thrust. The thrust axis when in the vertical position is approximately through the center of gravity. A generally U-shaped engine inlet duct is mounted in the airframe having an inlet opening facing forward and an outlet coupled to the inlet of the engine.

Abstract: Two tail control surfaces operable doubly as thrust-deflecting vanes are rotatably supported on respective lateral sides of a jet engine of a V/STOL aircraft. Each tail surface can be actuated to rotate about an axis parallel to the engine axis and also to rotate about an axis perpendicular to the engine axis. The tail surfaces can be placed in outer positions on respective lateral sides of the engine for high-speed flight to function as stabilizer surfaces and to be placed within the engine exhaust gas stream and, moreover, to be placed in an inclined state relative thereto thereby to deflect the stream downward for slow-speed or hovering flight.

Abstract: A superagile tactical fighter aircraft and a method of flying it are disclosed. The superagile aircraft is characterized by articulatable air inlets, articulatable exhaust nozzles, highly deflectable canard surfaces, and control thruster jets located around the nose of the fuselage, on the top and bottom surfaces of the propulsion system near the exhaust nozzles, and on both sides of at least one vertical tail. The method of operating the superagile aircraft comprises the step of articulating the air inlets and exhaust nozzles, deflecting the canard surfaces, and vectoring the thruster jets so that supernormal flight is attained. Supernormal flight may be defined as flight at which the superagile aircraft operates at an angle of attack much greater than the angle of attack which produces maximum lift. In supernormal flight, the superagile aircraft is capable of almost vertical ascents, sharp turns, and very steep descents without losing control.

Abstract: A thrust reversing system acting on a cold flow air duct of a turbofan-type turbojet engine is disclosed wherein the thrust reversing doors conform to a turbojet engine housing formed as a body revolution about a central longitudinal axis. The thrust reversing doors function to selectively divert the air passing through the cold flow air duct into a reverse thrust direction and also serve to vary the cross-section of the air duct. When the thrust reversing doors are in the forward thrust position, the downstream edges of the doors may be adjusted in a radial direction to vary the cross-section of the duct. The thrust reversing door is pivotable about a pair of axes, which may extend generally transverse to the longitudinal axis of the engine. The door is pivotally attached to a pair of link arms by a primary pivot which defines the first pivot axis. The link arms are attached to a fixed portion of a turbojet engine structure by a secondary pivot which define the second pivot axis.

Abstract: A fixed wing airplane having a turbofan engine mounted within its fuselage is equipped with communicating air-handling chambers, and pivoted panels positioned in the upper surfaces of the wings and stabilizers. The arrangement of air-handling chambers and pivoted panels supplies high velocity air through discharge slots tangentially to the upper surfaces of the wings and stabilizers, and air inducting slots on the same surfaces downstream from the discharge slots. Such manner of function causes a boundary layer of air to cling tightly to the upper surfaces, and this effect provides reduced pressure that produces vertical lift. Once in forward horizontal flight, the various components of the airplane function in conventional manner.

Abstract: An aircraft has two vectorable front nozzles each mounted in a bearing located within the fuselage near an adjacent wing. Each nozzle is rotatable from a first position in which exhaust air is directed downwards to a second position in which the exhaust air is directed rearwards. In the first position the nozzle resides within a cavity formed in the wing root to reduce nozzle drag when the aircraft is propelled by its rear nozzle only. The front nozzles rotate out of their respective cavities to the second position when they are used for forward thrust. Additionally, the cavity is extended to form a passage through which secondary air entrained by exhaust from the front nozzle operating in the first position adds to the vertical thrust and reduces suck down effects.

Abstract: An aerospace vehicle having multiple propulsion systems on a relatively rotatable flying wing capable of takeoff and subsequent landing with intermediate space flight in the manner of a conventional aircraft and rocket, respectively, comprising an elongated wing member having internal passenger and crew, cargo and fuel storage compartments. A plurality of propulsion systems are distributed about the wing member for providing thrust and aerodynamic control. The vehicle also includes rotating means for controlling the direction of the thrust of the propulsion systems relative to the longitudinal axis of the wing whereby to rotate the wing member relative to the direction of flight. The vehicle takes off and lands with the longitudinal wing axis being transverse to the direction of thrust and therefore to the flight direction in a manner similar to that of conventional aircraft.

Abstract: A nozzle for a gas turbine engine having a first fixed petal 44 and a second movable petal 46 which is pivotally mounted at a point intermediate its leading edge 46(a) and its trailing edge 46(b). Actuation means 48 are provided to move the nozzle between a first and a second position. In the petals first position, its leading edge 46(a) is positioned forward of and slightly radially inward of the trailing edge 50 of the exhaust duct 52, such that a small ejector gap 54 is provided therebetween and the trailing edge 46(b) approaches the trailing edge 44(b) of the fixed petal, such that the gap therebetween defines the exit area of the nozzle 36. In the petals second position (shown dotted), its leading edge 46(a) is moved radially inwards of its trailing edge 46(b) such that the exit area of the nozzle is defined by the area between the trailing edge 50 of the exhaust duct 52 on the second petal side and the trailing edge of the first petal 44(b).

Abstract: A gas turbine includes a change-over valve having a rotatable part and a static part. The valve is disposed between upstream and downstream compressors of the engine for selectively directing flows from the upstream compressor and an auxiliary inlet to the downstream compressor or an auxiliary outlet, the downstream static part of the valve being formed as a structural element of the engine casing from which extends forwardly a support member which carries bearings for supporting the forward rotating part of the valve and the casing of the compressor.

Abstract: A flying platform, propelled by at least one ducted fan causing a vertically downwardly directed airstream in and through a cylindrical duct. A vane system in the duct has two mutually perpendicular pairs of diametrically opposite first vanes, each extending in from the duct rim toward the center of the duct. Each pair of first vanes provides a pair of generally vertical walls parallel to a diametral line across the duct, and they define duct passages between the pairs of vanes and define quadrants between adjacent pairs. Each first vane has an upper, fixed, rigid portion and a variable camber flap depending therefrom. A first servomotor with linkages vary the camber of each pair of flaps, so that the camber of the flaps of each pair is at all times the same amount but in opposite directions. Preferably, there are also four second vanes, one bisecting each quadrant, and a symmetric pair of spoilers is mounted on each second vane.

Abstract: A cascade assembly for directing the gases externally of a jet aircraft engine in a forwardly direction when the engine is in a gas reversing mode. The cascade assembly comprises a plurality of cascade panel sections positioned in a side by side relationship over an opening in the engine nacelle. The panel sections have a plurality of spaced apart curvilinear vanes angled from the centerline of the engine. Longitudinal beams are positioned over the longitudinal edges and adjacent ends of at least one cascade panel section to secure it in place. The beam is "T" configured in the cross-section with feet or pads on each end to overlay the longitudinal outer edge and adjacent end surfaces of the cascade panel section or sections which it is securing in place. The pads or feet on the beam ends include apertures therethrough for securing the beams to aircraft structure. Both the cascade panel sections and beams are constructed of molded plastic or cured composite materials.

Abstract: By mounting a lift engine and a lift/cruise engine closely to the center of gravity of an aircraft and by orienting the respective engines such that the thrust axes thereof are arranged for ensuring that the vector sum of the lift engine thrust and the lift/cruise engine thrust pass through the center of gravity at all times, a fuel efficient aircraft can controllably takeoff and land vertically. To provide for vectoring the thrust of the respective engines, different nozzles are provided. Further, to provide for pitch, roll and yaw control, a vane assembly is coupled to the aircraft in such a way that it remains in alignment to the jet stream of the lift engine.

Abstract: One major problem associated with the design of high-speed vertical take-off or landing aircraft is the requirement to have the front vectorable nozzles of the aircraft deployed in the airstream which passes over the fuselage of the aircraft when they are in use. The nozzles tend to act as air brakes and thus seriously effect the forward speed and flight characteristics of the aircraft. This invention attempts to solve this problem by providing a vectorable nozzle which is rotatable about one axis between a first position in which it is stowed inside a cavity within the aircraft fuselage when not required, and a second position in which it is deployed into the airstream when required.

Abstract: A two-dimensional nozzle for directing the exhaust of a gas turbine engine includes two spaced apart vertical sidewalls (16), an upper flap assembly (18) and a lower flap assembly (20). The upper flap assembly (20) includes at least a dorsal flap (22) pivotable about a first fixed axis (24). The lower flap assembly (20) includes a ventral flap (28) centrally pivotable about a second fixed axis (30) for creating a dual throat exhaust flow path.

Abstract: By controlling the flow of the air over an airfoil, a lifting force can be achieved even in the absence of forward motion by the aircraft. The air flowing over the airfoil is forced into a chamber by a propulsion unit and the air entrapped in the chamber can be recirculated to a forward portion of the airfoil lifting surface, thereby increasing the lifting force of the airfoil. The lifting body has side members associated with the airfoil to channel the air over the airfoil. Outlets from the chamber are provided to direct the flow of air in any lateral direction for assistance with directed motion or for assistance with aircraft stability. Additionally, outlets in the bottom of the aircraft can assist in the vertical force exerted on the aircraft by forced air escaping therefrom.

Abstract: A method and system for improved performance of a V/STOL aircraft characterized by directing a major portion of exhaust gas flow from a propulsion system through a closed conduit means to exit through a thrust producing primary nozzle that includes turning apparatus for forming a bend for the exhaust flow downstream of the propulsion source; turning the exhaust flow while simultaneously bleeding-off through at least one secondary nozzle a second and minor portion of the exhaust flow from an outer portion of the bend downstream of the bend leasing edge to reduce the vortex formation in the bend and directing the bleed-off and exhaust flows adjacent each other and oriented in the same direction in all flight modes for recovery of the maximum thrust potential.

Abstract: A nozzle structure for a gas turbine power plant for a V.T.O.L. or S.T.O.L. type aircraft includes a main engine and at least one auxiliary engine; the efflux from the at least one auxiliary engine may be directed downwardly or alternatively horizontally through a convergent/divergent nozzle which may be closed off when the at least one auxiliary engine is inoperative.

Abstract: A vectorable exhaust nozzle 17 for a gas turbine engine comprises a fixed duct 21 and a cowl 22 pivotably attached to the duct 21 to facilitate rotation of the cowl 22 about a horizontal axis transverse to the exhaust stream issuing from the duct 21. The nozzle 17 further comprises a flap 23 pivotably attached to the lower downstream edge of the duct 21 for rotation about a second horizontal axis transverse to the exhaust stream and an actuation means 28 for rotating the cowl 22 and flap 23. The cowl 22 and flap 23 communicate via at least one link member 24. The actuation means 28 rotates the cowl 22 which, by way of the link members 24, rotates the flap 23 in the same direction. The nozzle 17 defined by the sidewalls 22a and the interconnecting curved wall 22b of the cowl 22 and the downstream edge of the flap 23, is thus vectored from a direction facing rearwards to a direction facing downwards.

Abstract: A compound helicopter shown in FIG. 1 of the drawings has wings 12 in addition to a helicopter rotor 14 and has twin powerplants 16 each including a low pressure compressor 18, a gas generator 20, a power turbine 22 driven by the gas generator and connected through a gearbox 32 to drive the helicopter rotor, and a variable area final propulsion nozzle 24 which receives the exhaust from the power turbine. Augmentor wing flaps 28 are provided on the wings and fed with air from the low pressure compressor for providing additional lift and thrust from the wings. The flaps 28 are pivotally mounted on the trailing edge of the wing and are movable to a position where the trailing edges of the flaps 28 obturate the flow through the gap between the flaps 28. In this position the flaps provide a means of decelerating the forward speed of the aircraft.

Abstract: An engine nozzle construction having a flap nozzle at the end of an engine exhaust duct, said flap nozzle variably controlling exhaust flow providing a primary flow path, said flap nozzle being movable to a position to direct the exhaust flow from said exhaust duct into a peripheral chamber, said chamber having exit openings around it providing for a secondary flow path for the exhaust flow.

Abstract: A valve for selectively changing the direction of flow of working fluid through a variable cycle engine which comprises a first and second compressor 14,16 spaced along a flow duct 26. The duct 26 having air intakes 42 leading to the second compressor 16 and outlets leading to nozzles 44. The valve comprising a sleeve 30 axially movable along the duct. The sleeve 30 having openings 31 in it in which are located doors 32. Links 36 are connected to each of the doors 32 so that as the sleeve 30 is moved axially the doors 32 are pulled open to open the air inlets 42 and the outlets and simultaneously obturate the flow duct 26. In a second position of the sleeve 30 the doors 32 and the sleeve 30 close off the air inlets and outlets and open the duct to allow the first compressor to supercharge the second compressor.

Abstract: A two-dimensional variable area convergent/divergent exhaust nozzle having the capability for wide throat area variation includes upper and lower spaced apart flap means. The upper flap means comprises an upstream converging flap having its rear edge hinged to the forward edge of a downstream diverging flap, wherein the nozzle is movable between maximum and minimum throat area positions by actuation means which includes guide means, such as cam tracks, for guiding the forward edge of the upstream flap to move downstream while simultaneously constraining both the upper flap means hinge joint and the rear edge of the diverging flap to move both downstream and closer to the engine axis. This type of motion permits large changes in throat area with minimal increase in the slope of the diverging flap permitting use of a shorter diverging flap. Preferably the forward and rearward edge of the converging flap move along circular arcs having the same center in order to minimize moments on the flap.

Abstract: The invention relates to a variable area nozzle for a turbo-jet engine. This nozzle comprises a convergent portion, formed by a fixed semi-shell (2) and a semi-shell (3) pivotal about a diametral axis (4a-4b); the fluid-tightness of the convergent portion is ensured by a substantially semi-circular seal (6) and by two longitudinal seals (7a, 7b). The nozzle can be used for example with an engine comprising a partial re-heat system of moderate output.

Abstract: A seal plate rests along the edge of a moveable flap surface and extends outwardly therefrom into contact with a stationary wall to seal the gap between the flap edge and the wall. The seal plate is hinged for rotation to one end of a pivotable support link which is hinged at its other end to the flap. The gas pressure load on the seal plate presses it against the flap surface and also tends to rotate the support link to press the outward edge of the seal plate against the stationary wall.

Abstract: A circulation controlled airfoil has a body structure with leading and trailing ends and upper and lower surfaces extending therebetween, and a cylindrical member disposed along the trailing end of the body structure between the upper and lower surfaces thereof so as to form a rounded, blunt trailing edge surface on the airfoil. A first blowing jet slot is defined between the outer surface of the cylindrical member and the trailing end of the body structure adjacent its upper surface. A second blowing jet slot is defined in a tubular wall of the cylindrical member. The latter member can be rotated to vary the distance of the second jet slot from the first jet slot and thereby adjust the point of separation of air flow along the airfoil from the outer surface of the blunt trailing edge surface formed by the cylindrical member. In such manner the lift generated by the airfoil can be optimized by providing blowing that is specifically tailored to given flight conditions.

Abstract: An exhaust nozzle for a gas turbine engine comprising a duct 17(c) extending along an axis and having at a dowstream end thereof a mechanism for varying the geometry and area of the nozzle. The mechanism 28 comprises an axially translatable member 28 which has a face 29 extending in a direction transverse to the axis of the duct 17(c) against which pressurized gases flowing through the duct acts to balance out the loads on the flaps. A plurality of flaps 38,43 are spaced circumferentially around the axis of the duct. The flaps 38 are pivotally attached to the axially translatable member 28 and are provided with a cam follower 40 that co-operates with a cam 37. The cams 37 are fixed relative to the duct 17(c) and thereby defines the attitude of each flap 38 relative to the member 28. Seal plates 41 and 45 cover the gaps between adjacent flaps 38 and 43 to the seal plates 45. A plurality of struts interconnect the member 28 and the second flaps of the pivotal attachment of the flaps 43 to the flap 38.