Abstract: A fixed geometry duct defining a gas turbine engine exhaust nozzle includes a plurality of circumferentially adjoining flat triangular facets and coaxial first and second openings at opposite ends thereof. A method of making the duct includes scribing a plurality of lines on a flat sheet metal plate to define the facets, and bending the plate at each of the lines to form the duct.

Abstract: An exhaust nozzle for a gas turbine engine includes a converging inlet duct disposed in flow communication with a diverging outlet duct at a throat therebetween. An ejection slot is disposed at the throat, and compressed air from the engine is selectively injected through the slot for fluidically varying flow area at the throat for exhaust gases from the engine.

Abstract: The present invention relates to a noise supressor assembly for a jet engine comprised of a plurality of conduit assemblies proximate the trailing edges of the wall members which capture a portion of an ambient gaseous stream flowing in an ambient flow for introduction into the hot core gaseous flow to thereby deform the interface between the hot core flow and the fan flow or ambient flow when there is no fan between the fan flow and the ambient flow or between fully or partially mixed core and fan flows and the ambient flow thereby mixing such gaseous streams to thereby reduce velocity of the hot core and fan flows and thus jet noise level.

Abstract: The air intake includes two main flaps (1, 2) facing each other and each pivoting about a pin (4, 5) adjacent to a wall (6, 7) extending the flap in question (1, 2) rearwards, and in which a first boundary layer bleed (8a, 8b) is arranged, the pins (4, 5) being substantially parallel to the plane of the wings or of the fuselage so that the flaps (1, 2) move perpendicularly to this plane, and a ramp (11) pivoting about a pin (12) adjacent to its leading edge (11a) by which it is adjacent to the wings and to the fuselage and substantially parallel to the pins (4, 5) is upstream of the flap (1) which is closest to the wings and with which it delimits another boundary layer bleed (13) of variable cross section.

Abstract: An actuation system for controlling the steerable nozzle of a missile or like vehicle is combined with an aerofin control system, both of which are driven in unison by associated drive motors and gear assemblies, one set for each aerofin. The nozzle steering system comprises two essentially identical yoke plates mounted along a plane generally transverse to the missile axis and oriented orthogonally relative to each other about the missile axis for pivoting the nozzle through mutually orthogonal axes, thereby achieving omni-directional steering. The yoke plates are coupled at opposite ends to pinion gears which are driven by the same gear assemblies which drive the associated aerofins. The arrangement permits common directional control of the steerable nozzle and the aerofins while maintaining the nozzle in a neutral direction when the aerofins are rotated to a missile roll control mode.

Abstract: The present invention relates to a method and apparatus for providing an operable divergent/convergent variable geometry exhaust nozzle for jet propelled aircraft. A multiplicity of hinged, overlapping, nozzle blades circumferentially surround the exhaust nozzle thereby providing a divergent cylindrical exhaust nozzle that may be convergingly reduced to a conical configuration by action of a remotely controlled solenoid.

Abstract: A propelling nozzle has upper and lower primary and secondary flaps which are disposed opposite one another at a mutual distance and which are sealingly movably guided between lateral wall portions of a four-cornered nozzle housing. The primary flaps are arranged pivotally about a fixed axis of rotation on the nozzle housing. The secondary flaps, in each case upstream of levers non-rotatably connected with the primary flaps, are pivotally linked to pivots situated on the side facing away from the nozzle flow. The secondary flaps change into the primary flaps with a surface section which is bent concentrically with respect to the pivots. The primary and secondary flaps are arranged in a four-cornered nozzle housing which is itself closed in. In each case the secondary flaps are arranged on the nozzle housing in an axially movable and angularly adjustable manner at the downstream end. The levers are formed on interior sections which are bent away from the primary flaps in a toggle-lever-type manner.

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: The invention is a propellant utilization system for flight vehicles operating in both the subsonic and supersonic speed ranges. In particular, the invention uses steam and water produced in the system to replace hydrogen as a coolant and for power generation. It also provides for the utilization or oxygen obtained from air captured by the air inlet instead of oxygen stored in the vehicle.

Abstract: A propulsion system for an aircraft capable of hypersonic flight combines a turbo-jet with a ramjet which are so arranged that the ramjet or jets are located directly adjacent to the aircraft body while the turbo-jet or jets are located away from the aircraft body so that the ramjet or jets is placed between the turbo-jets and the body. This arrangement makes the turbo-jets much more accessible for maintenance and exchange work. Both types of engines have a common air intake which is provided with flaps capable of guiding the body boundary layer through the ramjet when the latter is not in operation. When the ramjet is in operation, the air intake flaps form the air intake in such a way that boundary layer turbulent air is mixed with undisturbed incoming air for the ramjet while the air inflow to the turbo-jet is closed off altogether.

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 having a propulsion system which utilizes a dual fuel system having an inner tank for containing a cryogenic fuel and an outer tank surrounding the inner tank for containing a second fuel wherein the second fuel is a fuel having a low freezing point and a high boiling point which acts as an insulator for the cryogenic fuel in the inner tank. Both the inner tank and the outer tank are non-vacuum type tanks, and by surrounding the inner tank containing for example, liquid hydrogen, with pre-cooled liquid and/or gaseous hydrocarbon in the outer tank, excessive boil-off of the liquid hydrogen is prevented at high altitudes. By using this propulsion system and method, the outer wall of the outer tank is the skin of the aircraft, and the shape of the outer wall of the outer tank conforms to the aerodynamic shape of the aircraft.

Abstract: An improved jet engine two dimensional, asymmetric afterburner nozzle of the type adapted to be mounted on a jet engine suspended from an airfoil's wing spar structure, and characterized by its low profile configuration, simplicity of construction, and lack of interference with, or excessive intrusion into, the wing spar structural space within the airfoil; yet, which permits minimization of the included angle between the wing chord reference plane and the visual line-of-sight from the airfoil trailing edge into the jet engine nozzle while in its cruise position. More specifically, the present invention pertains to a simplified two dimensional, asymmetric convergent or CD nozzle construction, and an actuating mechanism therefore, which avoids the necessity to devote critical wing spar structural space to pneumatic load or pressure balance chambers, and wherein the nozzle may be shifted to a dry nozzle position--i.e.

Abstract: A method of reducing the destructive effects of a tornado, which has a rotary motion about a center and has at least one clear air inflow region at its periphery, comprises towing through the inflow region one or more fluid dynamic converters which impart a rotary motion to a column of air and thereby disturb the balance of the rotary motion of the tornado so as to reduce its intensity. The fluid dynamic converter comprises a cylindrical casing which is towed in a lengthwise direction by an airplane and has inside the casing a screw-like vane which imparts a rotary motion to the airstream flowing through the casing.

Abstract: A twin-engined VTOL/STOL aircraft comprising a rearwardly bifurcated fuselage 10 is proposed which in the event of failure of one engine 20 will allow the other engine 20 to produce a thrust which is not assymetric relative to the longitudinal axis of the aircraft. The fuselage 10 comprises a central front nose portion 11 and two side mounted engine nacelles 13, 14 which extend rearwardly to define spaced tail booms 15, 16. The engines 20 are preferably by-pass gas turbine engines in which the turbine exhaust gases are discharged through one or more nozzles 28 to the rear of the nose portion 11 between the tail booms 15, 16 on the center-line of the aircraft. The by-pass air is discharged through one or more nozzles 27 adjacent the longitudinal center-line of the aircraft. The nozzles 27, 28 are either swivellable, or other devices 34, are provided to vary the direction of thrust from the nozzles.

Abstract: A rotationally symmetrical supporting member provides lift in response to movement of air over its upper surface, and such air movement is produced by the impeller of a coaxially arranged drive unit, the base of which is connected to the supporting member so that counter torque from the drive unit imparts rotational movement to the supporting member. A carrier which may hold a load or supporting steering flaps is rotatably mounted in relation to the supporting means and to the driving unit.

Abstract: A propulsion/control system for aircraft of the vertical takeoff and landing type having a body without wings or tail and relying entirely on fluid streams for effecting liftoff, propulsion, and control. The body has an air duct with an inlet adjacent the rear end and a downwardly directed outlet at each side, an engine driven fan being disposed in the duct at the inlet and a cascade of adjustable vanes at each outlet. Operation of the fan causes air to flow into the inlet, through the duct, and issue in streams from the outlets, the reaction of such streams imparting lifting and flight forces to the body. By adjusting the cascades of vanes, the effects of the forces can be varied to control the movement of the body. To further control the movement and stability of the body in the air, additional adjustable elements may be provided.

Abstract: Aircraft engine exhaust is mixed with air and fuel and recombusted. Air is drawn into the secondary combustion chamber from suction surfaces on wings. Exhaust of the secondary combustion chamber is blown over wing and fuselage surfaces.