Abstract: Vertical lift in an aircraft is produced by driving a column of air downwardly, through an annular thrust-flow channel which is formed in the body (fuselage) of the aircraft. The aircraft also has an aerodynamic shape which is capable of developing lift responsive to forward flight. The annular thrust-flow channel is provided with a flow control mechanism which is capable of directing the developed air flow in varying orientations between a substantially vertical (axial) orientation for developing stationary, vertical lift (i.e., hovering) and a vectored (angled) orientation for developing a vertical component for producing lift and a horizontal component for producing forward (or rearward) flight, or flight to either side.

Abstract: A thrust directing mechanism to vector thrust and control discharge throat area with a number of vanes mounted across the passage. The mechanism includes a control link pivotally coupled to each of the vanes. The control link is selectively movable to correspondingly pivot the vanes and has at least two degrees of freedom corresponding to a two coordinate position. A desired orientation of the vanes may be determined as a function of the two coordinate position. The discharge exit area is contracted by adjusting convergence of the vanes. During convergence, the vanes are pivoted to various pivot angles selected to optimize thrust efficiency when contracting the throat area.

Abstract: A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine and afterburner sections and includes ports complementing the inlets in the offtakes to divert the core stream through the offtakes and passages to proportion the fan discharge air utilized for cooling purposes in the engine to cool the liner and walls of the offtakes and the engine components located downstream of the rotary drum while assuring separation of the core stream flow and fan air flow.

Abstract: A vectorable nozzle for a vertical lift aircraft comprising an array of lift flow deflecting vanes mounted in a frame hinged to an undersurface of the aircraft. The nozzle is formed by a plurality of telescopic shroud members which together with the vane frame are mounted at their forwardmost ends. The disposition of the vanes is such that the lift flow is directed downwards when the nozzle is extended. When the nozzle is retracted the flow is vectored rearwards to provide forward thrust. In this position the nozzle generates minimum aerodynamic drag from forward movement of the aircraft. The nozzle preferably is fully stowed within the aircraft, and concealed by surface doors when not in use.

Abstract: A system for enabling an aircraft to accomplish extremely short takeoffs and landings, which includes an integrated flight control system; a takeoff system; a landing system and a high thrust-to-weight propulsion system. The integrated flight propulsion control system includes a multi-axis thrust vectoring system. The takeoff system is operably engageable with the multi-axis thrust vectoring system. The takeoff system includes means for rotating the aircraft nose upwardly below stall speed without substantial use of thrust vectoring from the multi-axis thrust vectoring system. The landing system is operably engageable with the multi-axis thrust vectoring system. It includes means for de-rotating the aircraft from a high angle of attack to a main gear touchdown angle of attack sufficiently low to avoid scraping the tail of the aircraft.

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: An aircraft with automated means to transport. Spherical or one of its segments, without airfoils for lift or guidance. Means for flight are housed within the aircraft. The outer-most sureface is configured to disrupt the air-flow, over its surfaces, in flight. This, to reduce skin-friction and drag coefficients, and mollify heat build-up on the skins outer surfaces as speeds increase to and beyond mach 1. The weight of gas per unit volume, with temperature variations, is the means to reduce the gross-weight and adjust for temperature and weight changes during flight. Propulsion, within the propulsion component, is provided by turbojet engines. They are secured within an inner compression pod and an outer combustion pod. The compression pod and the attached vertical-air-duct, rotate through three hundred sixty degrees, as the means for directional guidance and direct thrust. Augmented power-thrust-tubes extend outward from the combustion pod to the mid-horizontal circumference of the aircraft.

Abstract: A nozzle for use on opposing ends of the rotor of a jet powered tri-mode aircraft is disclosed. The nozzle includes two thermally-controlled doors, which are moveable between an open configuration where hot jet engine exhaust is vented therethrough to propel the rotor in a helicopter mode, and a second closed configuration where the two doors are tightly sealed to provide a stable aerodynamic surface for the rotor when the jet powered tri-mode aircraft is operating in an airplane mode. The two doors are thermally-activated by an internal surrounding temperature, such that they remain open by the hot jet engine exhaust passing thereby in the helicopter mode, and remain shut by resulting cooler air when the hot jet engine exhaust is not routed by the two nozzle doors.

Abstract: First and second pylon flaps are located on aft portions of the first and second jet engine pylons, respectively. The first and second pylon flaps are moveable between retracted pylon flap angular orientations and extended pylon flap angular orientations. The first and second pylon flaps can assume only fully retracted angular orientations and fully extended angular orientations. When the T-tailed aircraft enters into a deep stall condition, the pilot will more than likely push the control column forward to its maximum position. This full forward movement of the control column commands the first and second pylon flaps to assume fully extended angular orientations. A first pylon flap controller controls the first pylon flap to move between the fully extended and fully retracted angular orientations, and a second pylon flap controller controls the second pylon flap to move between the fully extended and fully retracted angular orientations.

Abstract: An aircraft which is capable of safely landing during an emergency landing is disclosed. The aircraft has a safety device which includes a plurality of auxiliary engines. Each auxiliary engine is movable so as to vary the thrust axis in a range between a substantially horizontal direction and a substantially vertical direction. The safety device also includes a plurality of gas bags contracted and disposed at a lower portion of the aircraft body so as to be instantly expandable at a necessary time, such as during an emergency landing.

Abstract: An airborne vehicle generally comprises a body, a lifting mechanism for lifting the vehicle, and a steering mechanism operable by a user for steering the vehicle. The lifting mechanism comprises first and second counter-rotating propellers mounted in a front end and a rear end, respectively, of the vehicle body. The lifting mechanism further comprises a front air intake and a rear air intake mounted in proximity to and above the first and second propellers, respectively. The steering mechanism comprises a plurality of louvers mounted on a bottom of the vehicle body below the first and second propellers. The operator uses a steering mechanism in a passenger position to adjust inclinations of the louvers so as to steer the vehicle.

Abstract: A VSTOL aircraft powerplant comprises a gas turbine engine (1), a chamber (2) for receiving exhaust from the turbine section of the engine (1), and a jet propulsion nozzle (3) and vertical lift nozzles (4, 5) connected to the chamber (2). Blocker doors (6, 7) are provided for blocking flow of exhaust from the chamber (2) and thus diverting the flow to the vertical lift nozzles (4, 5). A high pressure air curtain is provided by ducts (9) to control th area of the ports to the vertical lift nozzles (4, 5). Control means coordinate and control the operation of the blocker doors (6, 7) and the air curtain to vary the total efflux between three configurations, namely all efflux occurrng through the jet propulsion nozzle (3) for wing-borne flight; all efflux occurring through the vertical lift nozzle (4, 5) for hovering; and some efflux, which is steplessly variable, occurring through both the vertical lift nozzles and the jet propulsion nozzle for transition between wing-borne and jet-borne flight.

Abstract: Apparatus and method for airflow vectoring control for an airfoil, a two dimensional jet, and the like. An airfoil or jet with a blunt open edge and a suction system for sucking air into the open edge. A blower system for blowing air out through the open edge. A control for changing the direction of flow through the open edge. A baffling arrangement for changing the magnitude and distribution of flow across the open edge.

Abstract: A method and apparatus for producing a thrust force from an annular axial stream of gaseous products fed to a nozzle with a supercritical pressure drop and acceleration to subsonic speed. In the nozzle, the direction of the subsonic annular stream is changed from axial to radial and the radial stream is divided into a plurality of opposing jets which collide in a braking zone and change direction back to axial for discharge into the ambient atmosphere. A change in thrust intensity (modulus) is effected by changing the flow rate of the radial jets and/or the flow rate of the axial stream discharged into the ambient atmosphere. Adjustment of the angle of the thrust vector is effected by changing the angle of discharge of the axial stream into the ambient atmosphere.

Abstract: A flying vehicle has wheels for highways, and a body and an engine. The body, engine and load define a center of mass (CG). Shrouded fans are located about the CG so as to produce, in conjunction with air jet redirection apparatus, the torques required to assume various attitudes. In one embodiment, an upper shrouded fan, with a diameter no greater than eight feet, produces an air jet, centered above the CG, for lifting the body. A second shrouded fan, smaller than the first, produces an air jet for lift, centered below the center of mass, on the longitudinal axis of the vehicle, forward of the CG. Third and fourth paired shrouded fans produce air jets for lift, centered below the CG, on either side of the longitudinal axis of the vehicle, toward the rear of the body. The paired second and third fans have equal diameters, no greater than half of the diameter of the upper fan, to keep the total width eight feet.

Abstract: A variable area exit for a gas turbine engine discharge nozzle having a generally rectangular outlet includes a pair of rotatable flaps which extend between opposing sidewalls of the nozzle. Each of the flaps are provided with a profiled cam track which cooperates with a cam roller mounted on an axially moveable shroud ring. The shroud ring is coaxially disposed about the nozzle axis so that translation of the shroud causes the flaps to rotate and the nozzle exit area to alter.

Abstract: A variable camber vane comprises a plurality of articulated spanwise segments which can be operated by a mechanism of pivoted links at one end. A plurality of such vanes may be arranged in a supporting frame to act a variable thrust deflector for the exhaust of a lift engine. In a VTOL or STOVL aircraft installation the vane array is mounted on the underside of the aircraft below a downwardly exhausting lift fan and the range of movement of the variable vane array is used to vector lift thrust between a mainly downward direction and a direction having a substantially rearward component.

Abstract: A vertical takeoff and landing heavier-than-air aircraft that includes a gyroscopic airfoil in the airstream of a ducted fan to cause vertical lift to the aircraft. The gyroscopic foil is both rotatably and pivotally attached to the aircraft such that it can be titled to provide directional control of the aircraft and, in at least one embodiment, has an adjustable airfoil forming part of the gyroscopic device such that the lift can be varied.

Abstract: A thrust unit for an aircraft having a lift unit for propelling the aircraft in upward flight. The lift unit includes a duct for directing air substantially downwardly, the duct being shaped so that air exhausting from its downstream end is in a stream having substantially the same cross-sectional dimension of the duct at the downstream end, and an air pump disposed for inducing a draught of air through the duct. In use, the draught of air exhausting from the duct can produce an upward thrust and is substantially non-convergent.

Abstract: A device for changing the direction of airflow inside a duct includes a curved panel portion with a leading edge and a trailing edge. The leading edge includes a spanwise extending rounded element which eliminates turbulent separation resulting from the change in airflow direction.

Abstract: In a VTOL or STOL aircraft in which a lift device is housed internally within the aircraft fuselage or wing an outlet nozzle is stowable within the lift device exit aperture. A pair of doors, which when closed conceal the aperture from the sides of the nozzle, and a third folding member form the forward side of the nozzle and support a frame carrying variable vanes which vector the lift thrust.

Abstract: A vertical lift and short takeoff airplane achieving a powered lift which is generated by deflecting downward on the order of nearly 90.degree. the slipstream from the driven propellors by means of the wing flap system of the airplane.

Abstract: A flying disc capable of vertical takeoff, hovering, or powered horizontal flight. The aircraft configuration comprises a circular disc-like airfoil-shaped wing structure having a convex upper surface and a concave lower surface with a leading edge and a trailing edge. At least one thrust-producing unit is attached at each of the leading and trailing edges, respectively. A plurality of other thrust-producing units are mounted symmetrically about the circular wing structure. Each thrust-producing unit has attached thereto a thrust deflector assembly for angularly adjusting the thrust produced by the thrust-producing unit, thereby allowing the aircraft to fly both vertically and horizontally. A substantial volume of helium gas is stored encompassing the inner upper hull of the aircraft, thereby giving the flying disc greater lift capacity. The outer skin of the upper surface consists essentially of a plurality of solar panels for delivering power to a multiplicity of devices.

Abstract: A vectorable nozzle mounting for an engine installation in a VSTOL aircraft in which hot gas nozzles are mounted on the airframe is described. A swivelable nozzle is mounted by means of a bearing on an intermediate fixed member such as a mounting ring on the airframe. The hot exhaust gas is discharged into the nozzle through a stub duct carried by the engine casing. Misalignment and movement between the duct and the nozzle is accommodated by movable sealing rings carried in the intermediate member which engage the outer surface of the duct. The sealing rings are spaced apart to form an annular chamber which is supplied with cooling air at a higher pressure than the pressure in the exhaust duct. The cooling air is arranged to cool the nozzle bearing and leakage passed the seals is of cooling air into the nozzle thus excluding hot exhaust gas from the engine bay.

Abstract: The aircraft comprises a rotor with a vertical axis arranged in a housing for generating a lift exceeding the weight of the aircraft. The housing is essentially shaped as a circular wing. A first way of guiding air is provided for controlling the air stream generated by the rotor, by means of which the position of the aircraft can be controlled in hovering flight. From hovering flight, the aircraft can be moved into a cruise flight, where the lift of the aircraft is generated aerodynamically by the circular wing of the housing and its forward thrust by a propeller. For the transition between hovering flight and cruise flight, a second way of guiding air is provided for controlling the pitch of the aircraft. The structure for the second way of guiding air is arranged outside a zone defined by the air stream of the rotor.

Abstract: An unmanned air vehicle capable of vertical take-off and landing, hovering and high-speed horizontal cruise flight. A forward centerbody houses an engine and carries a single rotor assembly having a plurality of propellers lying in a plane substantially perpendicular to the centerline of the forward centerbody. A coaxial aft centerbody is secured to the aft end of the forward centerbody and typically houses the vehicle avionics. A plurality of stators extend outwardly of the aft centerbody, in a plane substantially parallel to the propellers. A single toroidal duct surrounds the rotor assembly and the stators and is secured to the stators. A plurality of movable control vanes are secured between the duct and aft centerbody aft of the stators. A flight control system, typically housed in the aft centerbody, controls the engine and the vanes to cause the vehicle to selectively move upwardly, downwardly, hover or translate to forward, horizontal, motion with the rotor in a plane within 80.degree. of vertical.

Abstract: An improved rotary wing aircraft shrouded propeller ducted tail assembly utilizing the flow pattern of the propeller slip stream exiting from the outlet end of the duct for flight control by means of movable slip stream deflecting surfaces. Three vertically extending deflecting surfaces are pivotally supported at the outlet end of the duct rearwardly of the propeller comprising a vertically extending, elongated rudder surface pivotally supported for rotation about a vertical axis on the duct centerline and a pair of duct sidewall flaps each pivotally supported by hinges mounted on the respective opposite duct lateral sidewalls for obtuse angular rotation between a position extending outwardly and perpendicularly of the duct sidewall on which it is hinged and a position extending through an opening in the duct sidewall of which it is hinged to protrude transversely of the duct interior.

Abstract: A system for augmenting yaw control in an aircraft is described which comprises first and second thrust nozzles disposed on the upper surface of the aircraft forebody aft of the forebody nose apex a distance of about 0.5 times the forebody diameter at about 45.degree. to either side of the symmetry plane of the forebody, each thrust nozzle oriented to direct a fluid jet at an angle of about 10.degree. from the surface of the forebody and generally rearwardly toward the symmetry plane at about 60.degree. .+-.10.degree. to the symmetry plane, and a source of pressurized fluid operatively connected to the thrust nozzles for generating the jets.

Abstract: A yaw vectoring blade which is alternatively recessed from and extended into an airflow path of an exhaust nozzle of an aircraft gas turbine engine. The yaw vectoring blade is provided with a housing cavity located in a divergent flap of the exhaust nozzle which provides a recess from the airflow path. Actuating means connected to the yaw vectoring blade can move the yaw vectoring blade into and out of the airflow path to produce a desired yawing moment.

Abstract: The invention is a propulsion system for a V/STOL type aircraft. In detail, the invention comprises a turbofan engine including a fan section, compressor section, combustion section, turbine section and nozzle section. The turbine section comprises a low-pressure turbine portion coupled to and driving the fan section and a high-pressure turbine portion coupled to and driving the compressor section. A lift fan is coupled to the fan section by means of a drive shaft. A clutch is incorporated for decoupling the lift fan from the fan section. A mechanism is incorporated for extracting additional power from the low-pressure turbine portion of the turbine section to drive the lift fan that augments the basic engine thrust for V/STOL operation.

Abstract: An engine and lift unit for rotary wing aircraft together with means for balancing of the rotational torque of the said wings is shown. The rotational torque is balanced by a blower propeller, disposed horizontally below the rotor, inside an enclosure including a vertical duct surrounding the blower propeller and whose lower open end exits under the fuselage of the aircraft. A horizontal duct opens into an intermediate zone of the vertical duct and exits out the rear of the aircraft. An adjustable shutter assembly is disposed in the junction of the two ducts allowing the creation of two adjustable air flows, one directed vertically downwards and the other directed towards the rear of the aircraft. The aircraft also has fixed wings, flaps, rudders and controls so the pilot can operate the aircraft in flight.

Abstract: Increased aircraft control is achieved by combining reverse thruster operation with splay capability. Each of the four door sets has a pair of vanes controllable to various parallel positions. Maximum opening at 26.degree. from the vertical decreases in each direction from the maximum position. The vanes may be controlled to effect yaw and pitch control while maintaining a constant total effective flow area. Back pressure on the turbine is thereby unaffected.

Abstract: Increased aircraft control is achieved by combining reverse thruster operation with splay capability. Each of the four door sets has a pair of vanes controllable to various parallel positions. Maximum opening at 26.degree. from the vertical decreases in each direction from the maximum position. The vanes may be controlled to effect yaw and pitch control while maintaining a constant total effective flow area. Back pressure on the turbine is thereby unaffected.

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: 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: 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: A flight system capable of passively stable hover and horizontal translatory flight, comprises an apparatus defining a vertical axis, and including multiple ducts with substantially vertical axes in hover mode, spaced the axis; fluid momentum generators in the ducts to effect flow of fluid downwardly in the ducts in hover; and fluid flow deflector structure in the path of the flowing duct fluid, and angled to deflect the fluid flow away from the axis, in such manner as to provide stability in hover of the apparatus, as well as stability when the entire device is tilted through approximately 90.degree. to execute horizontal translatory flight.

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 thrust reverser assembly is disclosed for a wing mounted gas turbine engine exhaust nozzle having a fixed outlet for discharging exhaust gases over a surface of the wing. The assembly in accordance with a preferred embodiment includes a deflector having forward and aft ends, and first and second sides joined together by a base. The deflector is positionable in a stowed position around the exhaust nozzle so that the aft end is disposed forward of the nozzle outlet for allowing substantially unobstructed discharge of exhaust gases therefrom, and in a deployed position for changing direction of exhaust gases for thrust reversal. Two pairs of first and second bellcranks are positioned adjacent to respective ones of the deflector sides and means are provided for rotating the bellcranks for moving the deflector between the stowed and deployed positions.

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 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: A flexible fairing 13 is provided which includes an aerodynamic surface 20 composed of a plurality of closely spaced, telescopic fairing members 14 and a moveable fairing panel 18. One end 15 of each fairing member 14 is pivotably secured to a divergent flap 11 of a thrust vectoring nozzle, and the other end 17 of the fairing member is pivotably secured to the fairing panel 18 which is slideably mounted to the static structure of a nozzle 19 of a gas turbine engine. The flexible fairing 13 adjusts to accommodate both translational and rotational movement of the divergent flap relative to an airframe fairing 10, thereby maintaining an aerodynamic surface 20 between the airframe fairing 10 and the divergent flap 11 of the nozzle.

Abstract: A thrust vectoring axisymmetric convergent divergent variable exhaust nozzle is provided with a universally pivoting joint between the divergent and convergent flaps and actuating the linkage mechanisms for changing the divergent nozzle section from axisymmetrical to asymmetrical by pivoting the divergent flaps in the radial and tangential directions with respect to the axisymmetric nozzle centerline in a controlled manner.

Abstract: A vectorable gas turbine engine exhaust nozzle including deployable angled flow deflectors for providing thrust vectoring in the yaw direction. In one embodiment the deflectors are pivotally deployed in the diverging section of a two dimensional nozzle with the use of either electromechanical or pneumatic rotary actuators. The deflectors are preferably employed in a two dimensional convergent divergent exhaust nozzle which includes a means for varying the size of the throat and a means for providing pitch thrust vectoring.

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 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: Control apparatus for effecting control of thrust magnitude and thrust vector angle for aircraft of the short take-off and vertical landing type known by the acronym STOVL comprises a fixed housing (10), a manually movable stick member (7) supported with respect to the fixed housing (10) and arranged to provide a throttle input, the stick member (7) including a grip (8) to enable it to be gripped and moved manually relative to the fixed housing (10), and a rotatable collar (9) arranged to provide the thrust vector angle input. Preferably the grip includes an upright hand-datum flange (13) for positively laterally locating a controlling hand and the hand-datum flange (13) is located at one extremity of the grip (8) and the collar (9) is located at the other extremity of the grip (8).

Abstract: A yaw and pitch thrust vectoring exhaust nozzle (10) includes upper and lower divergent flap assemblies (22, 24) each divided by oppositely skewed diagonal hinges (58, 60). Vertical sidewalls (27, 28) are also hinged to open the nozzle outlet laterally during yaw thrust.