Abstract: The invention is a propulsion system for a lighter-than-air vehicle. In detail the propulsion system includes a pylon having a longitudinal axis and first and second ends, the first end of the pylon rotatably mounted to the vehicle and the second end extending outward from the vehicle. The pylon is rotatable about the first end in a plane perpendicular to the longitudinal axis of the vehicle. A thrust producing assembly is mounted on the second end of the pylon and is rotatable about an axis of rotation in a plane perpendicular to the longitudinal axis of the pylon. A powerplant assembly is coupled to the thrust producing assemblies to provide power thereto. An actuation system is provided for rotating the assembly about the axis of rotation. A second actuation system is provided for rotating the pylon about the first end.

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: Two arms rotatably mounted in slideable abutment with an interior wall of a nozzle. The arms extend from a common axis of rotation, and each includes a bump having a crest running radially from the axis of rotation to the tip of the arm. Together with the opposing ceiling and adjacent sidewalls of the nozzle, the arms define the moveable throat of the nozzle. The ceiling of the nozzle opposite the arms is contoured so that rotation of the arms changes the area of the nozzle throat while changing the direction of fluid medium flowing through the nozzle. The arms are connected by a linkage which coordinates their movement. Coordinated rotation of the arms can simultaneously change the throat area of the nozzle and the direction of fluid flow, or change either the throat area or the direction of fluid flow while keeping the other constant.

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: Exhaust vectoring control for gas turbine engines having an exhaust nozzle mounted on a ring that is positionally controlled by a plurality of actuators in response to pitch and yaw commands uses signal processing to convert pitch and yaw signals into actuator extensions based upon stored coordinates identifying the location of each actuator connected to the ring in relation to the X, Y and Z reference axes of the engine. The computation of these coordinates takes into account the orientation of the ring. The largest actuator change is selected and limited to a stored maximum allowable change in extension for a fixed or set time interval, such as a signal processor cycle, thereby limiting actuator vector rate. The limited change is divided by the largest computed extension change, producing a ratio or factor that is multiplied by the computed changes for the other actuators, producing a set of actuator signals that are simultaneously applied to their respective actuators for the processor cycle.

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: A helicopter anti-torque control system which relies on engine exhaust. Included is a force generating apparatus and a force directing apparatus. The force generating apparatus is at least partly driven by engine exhaust. The force directing apparatus takes outside air delivered to it by the force generating apparatus and directs it from the helicopter as a right-side or left-side force.

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: A fluid control apparatus for proportionally directing fluid from a single conduct to multiple exhaust ports around the periphery of the duct. A controller is provided which is rotatably supported in the duct by an axial shaft. The shaft supports a radial barrier vane extending along its length and a helical vane forming a single 360.degree. helical wall surrounding the shaft. Rotation of the controller exhaust to shaft axis directs the fluid to the appropriate exhaust ports according to its angular position.

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: 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: The airborne air cleaning station features a dirigible supporting a gigantic collector hood exteriorly mounted thereto, and an enlarged housing having a plurality of different types of air cleaning devices contained therein. The collector hood funnels polluted ambient air into an air intake system that places the on-board air cleaning devices in fluid communication with the collector hood. Sensors within the air cleaning station analyze an incoming air flow to determine the pollutants which need to be removed from the local atmosphere. Then, an automatic control system actuates automated valves of an on-board piping system to route incoming air to those air cleaning devices which are best equipped to remove whatever particular pollutants have been detected by the sensors. The inclusion of a plurality of different air cleaning devices, such as wet scrubbers, filtration machines, cyclonic spray scrubbers, etc. advantageously equips the airborne air cleaning station to deal with a wide variety of pollutants.

Abstract: A hybrid electric vehicle (10) capable of ground travel and air travel is described. The vehicle provides for movement over the ground by wheel motors (20) mounted at each of four ground engaging wheels (14 and 16). The wheel motors are supplied with electric power by a battery pack (24) or an electric generator (32) powered by a combustion engine (22). The combustion engine is also geared to vertically oriented ducted fans (40) and a horizontally oriented ducted fan or propeller (76) for providing the vehicle with the capability of travel through the air. Pressure jets (62), supplied with compressed air from a compressor (66) driven by the combustion engine, augment the lift of the ducted fans and provide steering for the vehicle. The vehicle can also be provided with photo-electric cells (82) for supplying a portion of the electric power for the vehicle.

Abstract: An improved control system for a rotary wing aircraft having a tail assembly comprising an annular duct within the interior of which a variable pitch propeller is concentrically mounted for rotation forwardly of movable surfaces for deflecting the slip stream generated by the propeller transversely of the duct as will provide transversely directed thrust forces for amounts required to counteract rotor torque and provide directional control of the aircraft in azimuth.

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 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: Tapered disc rotatably mounted in the exhaust duct of a propulsion system. The disc can be rotated about an axis normal to the yaw plane. A disc bump projects from both the upper and lower surfaces of the disc, and extends diametrically across it. When fluid is flowing through the exhaust duct, the bump, together with the opposing surfaces of the exhaust duct, chokes the flow and causes a sonic plane to be formed at the bump. The supersonic flow downstream of the disc bump remains approximately normal to the bump for angles of rotation of up to 20.degree. from normality between the bump and the upstream flow. Rotation of the disc thus causes deflection or turning of the fluid flow. The resultant thrust vectoring enables the yaw of the propulsion system and, therefore, a vehicle containing the propulsion system, to be controlled.

Abstract: A glide missile is provided with trimming devices for affording a positive ngle of incidence. The trimming devices are controlled by the combination of a fluidic element through which ram flows and a gyroscopically controlled shutter.

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: The present invention relates to an apparatus for controlling an air cushion vehicle (trade name, Hovercraft) of a vehicle to be driven by air flowing pressure, in which rudders are provided along both side walls of a propulsion fan duct, the rear sides of the rudders are bent toward the outside of the propulsion fan duct to perform the abrupt braking at the time of linearly moving and reverse moving of the air cushion vehicle, and the handle column for turning the direction is tiltably provided to easily move reversely the air cushion vehicle by the same handle steering operation.

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: An improved thrust vector control system for steering and controlling an aerospace vehicle propelled by a reaction type motor. The improved thrust vector control system simultaneously rotates and laterally translates the reaction motor with respect to the longitudinal axis of the vehicle. This complex motion of the reaction motor generates sufficiently large control moments that allows the reaction motor to be moved very close to the center of gravity of the vehicle. As a result, the vehicle can be shortened and the structure that is typically required to position the reaction motor at a swivel point farther aft eliminated.

Abstract: To quickly change rocket flight direction immediately after a rocket has been launched without increasing the wing area, the rocket flight direction control system comprises four steering wings for controlling rocket flight directions; four deflectable nozzles for jetting combustion gas backward to generate rocket thrust; a controller for generating steering control signals; and at least one actuator for actuating the deflectable nozzles in response to the steering control signals in synchronism with steering motion of the steering wings. Further, when the deflectable nozzle is divided into two, fixed and movable, nozzles, the diameter of the outlet end of the fixed divergent nozzle of the overexpansion type nozzle in matched with that of the movable nozzle for prevention of gas leakage through a gap between the two nozzles.

Abstract: An improved structure for the shrouded propeller tail duct or "ring tail" of a rotary wing aircraft providing rotor torque counteracting and aircraft yaw control forces in all flight conditions of hovering and high speed cruising flight. The rear portion of one lateral side of the shrouded propeller duct comprises a plurality of overlying arcuate segments that are pivotally supported for rotation relative to each other about a vertical axis between a retracted position for high speed flight in which the segments are in a mutually overlying position constituting one side of the duct and an extended position in which the segments are in a mutually adjoining relationship with their edges only overlapping and extending obliquely transversely of the duct interior in the form of a continuous, rearwardly projecting and transversely extending arcuate extension of the interior wall of one side of the duct.

Abstract: A vehicle capable of omnidirectional movement employing a jet engine and a plurality of directional jet nozzles communicating with said engine, and a single controller means united with said nozzles to cause omnidirectional movement of said vehicle and control the acceleration and deceleration of said vehicle.

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 seal for preventing extremely hot gases from passing between a movable engine ramp and an engine splitter wall in a hypersonic aircraft. The seal moves with the engine ramp, in a direction parallel to the surface of the splitter wall. The seal includes a first flange which makes sliding contact with the outer engine ramp surface and is attached to a flexible sealing portion that fills the gap between the ramp and wall. The sealing portion maintains sliding contact with the wall as the gap changes dimension due to variations in the ramp's temperature. The attachment region can be a concave surface to radiate the seal's heat. In a second embodiment, the seal includes a second flange through which the seal is attached to the cooler side of the engine ramp.

Abstract: A variable area, convergent-divergent (10) nozzle for directing the flow of exhaust gas from an aircraft turbine engine to achieve thrust vectoring about yaw, pitch and roll axes includes a convergent section (16) and a divergent section (18) each comprised of hingedly connected planar members (201-214, 301-322) selectively positioned by actuators (101-114) for defining deformable gas directing flow ducts.

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.

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: The invention is directed to a thrust vector control for aircraft with one or more jet engines whose thrust nozzles have an adjustable size exist cross-section, each of the jet engines having a ring rudder axially spaced behind the engine and movable about at least one pivot axis extending substantially perpendicular to the engine's longitudinal axis. A substantially planar rudder plate is secured diagonally in the inside cross-section of the ring rudder for each plane defined by each pivot axis and the longitudinal axis of the engine. The rudder plate or plates each consist of a material which is stable at high temperatures without supplementary cooling and which is mechanically loadable, and the connection between the rudder plate or plates and the ring rudder each include a layer of elastic and thermo-insulating material.

Abstract: A VTOL aircraft having a fuselage with fixed ring wings on either side thereof. Each ring wing has a rearwardly extending nacelle associated with it. Each nacelle has a ring tail empennage at its after end and a propulsor fan in its nose operating in the bore of its associated ring wing. The propulsor fans provide propulsion thrust for conventional flight in which the flow created over the lifitng surfaces due to forward velocity of the aircraft generates lift for flight. The propulsor fans operate to induce a flow over the lifting surfaces to generate lift for VTOL flight without a requirement for forward velocity by the aircraft. Aerodynamic control means such as spoilers are provided in the ring wings and empennages for pitch, roll, and yaw control in conventional flight.

Abstract: Control means and method for steering an aircraft is disclosed. The aircraft includes engines positioned on opposite sides of its longitudinal axis. The method comprises: selecting an aircraft heading; sensing a deviation from said heading; and varying the thrust of at least one engine in response to the sense deviation.

Abstract: An automotive vehicle is subject to attitude control input impulses effective only with respect to a roll axis and a selected one of a pitch and yaw axis. A selected and controlled sequencing of roll attitude control allows attitude control also of both the selected one axis and the other of the pitch and yaw axis for the vehicle.

Abstract: A flying disc aircraft includes a symmetrical body housing pilot and/or passenger seating apparatus above, a thrust-generating apparatus below, and a rotation inertia disc located therebetween. The disc rotates within the body in a plane normal to the axis of symmetry, and provides inertial stability for the aircraft through a gyroscopic effect. Directional control is achieved by means of mechanical linkage elements connecting a control stick at the pilot seating apparatus with the thrust-generating apparatus, the linkage allowing the pilot to orient the thrust at various angles relative to the aircraft axis of symmetry. Lift occurs when ambient air is induced, by virtue of the thrust-generating apparatus, to flow over the disc. In an alternate embodiment, lift is generated by the thrust-generating apparatus, and a shroud located beneath the apparatus is employed for redirecting resulting thrust to therefore facilitate directional control of the aircraft.

Abstract: An anti-torque system for use in a helicopter has an aft mounted horizontal fan submerged within a fuselage mounted, upward facing plenum. The fan operates off the mainpower source. The plenum has two controllable exit ports for counter torque control, fuselage pitch control and yaw control. The controllable exit ports are located along the longitudinal direction of the fuselage and each are substantially opposite each other. One port has a sufficiently sized area to effectively offset the torque of the main rotor while the other port has a sufficiently sized area to effectively provide autorotative yaw control. Both ports can be used simultaneous or singly.

Abstract: A boundary layer thrust vector control nozzle (10) has a housing (18), the aft end of which has attached a control vane assembly (12). The control vane assembly includes two brackets (78, 80) which receive two vanes (86,88) such that the vanes are in spaced parallel relationship and extend across the exhaust opening. The vanes have equal but opposite angles of attack and are adapted to generate large side forces in a perpendicular plane and small side forces in a plane parallel to the vanes. The nozzle includes four sets of control ports (44, 46) for deflecting an exhaust plume to produce the large and small side forces also to produce significant roll moments.

Abstract: A steering apparatus for steering propulsion devices such as a propeller shaft and rocket exhaust and for aiming devices such a fire hoses and lasers. The steering apparatus provides a rotational component and a tilting component to the orientation of the steered device.

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: Rocket booster motor vectoring system and method for shortening take-off distance of aircraft, the aircraft being airborne before it is going fast enough for its conventional controls to provide adequate stability and control. A rocket booster motor (52) is coupled to aircraft (50) by means of thrust arm link (56) is pivotal engagement with the aircraft and fixed to the booster, and coupled by rearwardly positioned links (62, 64, 66) having ball and socket joints at both ends, one end being connected to the aircraft through aerodynamic surfaces (68, 70) or through actuators (124, 126), the aerodynamic surfaces being operable by conventional systems within the basic aircraft, and the actuators also being operated by motion sensing systems within the aircraft to vector the thrust of the booster to provide stability augmentation of the aircraft during the boosted launch phase to provide pitch, roll, and yaw control.

Abstract: The present invention provides a single seat aircraft having the capabilities of vertical takeoff, landing and hovering operations utilizing the X-Wing as a conventional helicopter rotating wing. After transition to forward flight following takeoff, the rotating wing is stopped and becomes a fixed wing of "X" configuration. The aircraft utilizes two engines within the fuselage, one engine being positioned vertically above the other along the longitudinal axis of the aircraft, the particular arrangement of engines allowing aircraft size and weight to be substantially reduced.

Abstract: A control force generator for an aircraft using circulation control to a selectively produce lift on an otherwise non-lift surface. The generator employs a novel, double-slot single Coanda surface arrangement for selectively generating the aerodynamic lift.

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: Helicopter antitorque auxiliary propulsion system comprising a propeller attached to the tail boom adapted for powered rotation to create a directed air flow rearward of the helicopter, including a duct encircling the propeller and a pair of stabaron doors hingedly mounted in the ducted airstream to divert the air flow at high speed for directional control and to close at low speed and allow the air flow to be diverted through openings in the duct for directional and antitorque control.

Abstract: The steering of a jet propelled flying body is improved by positioning jet eflector flaps into the propulsion jet for deflecting the propulsion jet. The deflector flaps can steer the flying body automatically in response to a flight control unit either alone or as a support steering system for the control surfaces of the flying body. The jet deflector flaps are arranged in the jet nozzle in a cross or star configuration and preferably near the periphery of the jet nozzle.

Abstract: A high wing, twin jet gyrodyne having air jet reaction, contrarotating rotors powered with bypass air from twin turbofan engines. Tail pipes from the turbofan engines are disposed parallel to and at opposite sides of a longitudinal duct for discharging bypass air rearwardly. Control valve means can control supply of bypass air selectively to the hollow rotor mast for driving the rotors and to the longitudinal air discharge duct. The aft portions of the tail pipes and of the air discharge duct are connected by a horizontal stabilizer and rudders are located in the slipstream discharged from the tail pipes and the air discharge duct. The wings have drop tip sections providing flotation outriggers in their downwardly projecting positions.

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.