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.

Abstract: A large cylindrically-shaped balloon-like structure having hemispherical ends with fins utilized in conjunction with airflow thereacross based upon Bernoulli's principle for maneuvering and maintaining stability. The balloon is compartmentalized, contains a uniquely designed structural support system, and contains pumps for evacuating the air therein. The structure may be used for any lifting application. In particular solar-energy is collected through a transparent portion of the structure and reflected from shaped surfaces that direct solar energy on energy converting panels. The electrical energy generated is utilized to operate an evacuation system, while the remainder of the electrical energy is beamed by microwaves to a receiving station on earth.

Abstract: A duct 11 for an aircraft comprises a flexible panel member 18 which is normally held in a non-fluid conducting condition adjacent the surface of the aircraft body by biass tension means 12, 13, so as to define a substantially continuous surface. On introduction of fluid pressure between the panel and the aircraft body, the panel member is inflated to overcome the biass of the tension means 12, 13, and to expand to a fluid conducting condition of relatively large cross-sectional area, upstanding from the surrounding aircraft surface regions.

Abstract: A vectorable nozzle 17 comprising a fixed first duct 21 a rotatable second duct 22 scarfed at its rear end and a rotatable third duct 23 scarfed at its front end. The second and third ducts 22,23 are mounted in bearings 24,26 respectively and the bearing 26 is constrained to swing bodily about trunnions 29, the axis of which lies transverse to the ducts 22,23, and a screw jack 32 is provided to rotate the bearing 26 about the trunnions 29. The second and third ducts 22,23 are provided with means to rotate them in opposite directions in syncronism with the rotation of the bearing 26 in the trunnion 29.

Abstract: A propulsion system for an airplane to permit it to achieve vertical and/or short take-offs and landings. The propulsion system is integrated into a wing/nacelle unit and includes a thrust vectoring system. A separate flow turbofan engine is mounted in each wing/nacelle unit. A system of three flaps is located at the rear of each wing/nacelle unit for deflecting the turbofan engine exhaust downward, rearward, or any angle in between. These three flaps are arranged to provide a main thrust nozzle in the horizontal flight position without any additional flaps between them. One flap is located at the wing/nacelle upper surface trailing edge. Two slots are provided at the leading edge of this flap. The upper forward most slot is provided as an exit nozzle for the engine turbine exhaust, which is shrouded from the fan exhaust. The second of these two slots removes a portion of the high energy fan exhaust from the fan discharge duct and ejects it over the flap upper surface.

Abstract: A jet aircraft is provided of the vertical or short take off and land (VSTOL) type which is a stable and controllable in all flight attitudes. The aircraft exhibits a high engine thrust/weight ratio which enables it to achieve shorter take-off, shorter landing distances and faster climbs as compared with prior art aircraft of the same general type. The aircraft includes two jet engines mounted side-by-side in its nose which assist in achieving smooth variation in cross-sectional area so that the area rule is not violated, and this enables efficient flight speeds in the sonic vicinity to be achieved. The exhaust of each engine of the aircraft is controlled by a thrust deflector and associated air foil array, the thrust deflector being deflected downwardly at an angle of substantially 75.degree.

Abstract: An aircraft includes an aircraft body portion 10, a wing portion 14 attached to the body portion by means of an intermediate portion 15 whose thickness diminishes outboard of the body portion to blend with the wing portion. The intermediate portion 15 comprises upper and lower surfaces diverging rearwardly from a leading region to a region of maximum divergence. The aft portion of the intermediate region is cut away to receive propulsion jet outlet 16 which is shaped to be within a rearward projection of the region of maximum divergence of the intermediate portion. The propulsion outlet jet 16 may be directed downwardly to generate a lift component.

Abstract: A jet propelled aircraft of the kind in which propulsion jets are directed over the top surface of the wing so as to cause additional lift as a result of the supercirculation induced on the wing and the deflection of the jets downwards, due to the Coanda effect, immediately downstream of the wing is provided with two longitudinal surfaces projecting from said top surface so as to form a single surface ejector system. The wing of the aircraft has a fixed front part which occupies a minor portion of the wing chord, and a movable rear portion which is articulated to the fixed portion about a substantially transverse axis and can be inclined downwards relative to the fixed part. The portion of the wing between the two longitudinal surfaces may be provided on its trailing edge with a movable attitude control surface of the aircraft.

Abstract: A propulsion system for vertical take off and landing aircraft includes a forward compressor fan (40) and an aft compressor fan (42) downstream of the forward fan and in series flow communication with the forward fan. The forward and aft fans are positioned in a central duct (26). A gas turbine engine (44) is in series flow with the forward and aft fans for driving the fans. The forward fan, aft fan and turbine engine are interconnected by a common shaft (50). A forward diverter structure (100) is positioned downstream of the forward fan and is movable between a first position for diverting exhaust from the forward fan downwardly relative to the longitudinal axis of the aircraft while simultaneously permitting the introduction of air behind the forward diverter structure but ahead of the aft fan and a second position wherein the exhaust from the forward fan is channeled through the aft fan and turbine.

Abstract: An aircraft propulsion system is disclosed having an exhaust nozzle structure having an exhaust deflection structure extending within an exhaust duct to direction exhaust flow along selected flow paths. In its preferred embodiment, the exhaust deflection structure is a variable geometry deflection structure having a distal end portion which is movable, relative to adjacent aircraft structure, within an exhaust duct whereby the exhaust deflection structure is positionable as an extension of an upper, aft wall portion of the exhaust duct. In the preferred embodiment, the exhaust nozzle structure includes a guide structure or nozzle segment, connected to the exhaust deflection structure, which is translatably mounted to adjacent aircraft structure for permitting fore and aft movement of the nozzle segment along the aircraft structure.

Abstract: An improved pressure balanced nonaxisymmetric high aspect ratio afterburner convergent nozzle of the type adapted to be mounted on a jet engine suspended from an airfoil's wing spar structure, and characterized by its simplicity of construction, ease and reliability of operation, and improved simplified sealing characteristics; yet, which permits substantial reduction of the included angle between the wing chord reference plane WCRP 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 pressure balanced nonaxisymmetric high aspect ratio afterburner convergent nozzle construction which permits of simplified, highly effective sealing arrangements and wherein when the nozzle is shifted to a dry nozzle position--i.e., the cruise position--the trailing edge line-of-sight into the nozzle is maintained at a minimum angle, preferably on the order of from about 5.degree. to about 10.degree.

Abstract: An aircraft is disclosed having a jet engine whose exhaust stream flow rearwardly from above the trailing edge of a main wing of the craft, and having an auxiliary airfoil which is lower than and offset rearwardly with respect to the wing and acts during takeoff to augment thrust and lift, and during braking and landing to increase drag and lift. The airfoil is mounted for adjusting movement between a cruise position in which it is generally parallel to but lower than and spaced from the wing and one or more inclined positions for takeoff, landing and braking in which the airfoil has its leading edge spaced rearwardly and downwardly from the trailing edge of the wing and defines with that trailing edge a gap across which the jet engine exhaust stream flows in a relation drawing air through the gap from under the wing.

Abstract: A gas turbine engine exhaust nozzle assembly having vertical thrust capability comprises a two-dimensional converging/diverging nozzle and a veer flap for forward thrust operation and a rotatable hood type deflector for vertical thrust operation, wherein the forward edge of the veer flap is attached to the downstream edge of the deflector hood. During forward thrust operation, the hood and rear edge of the divergent flap portion of the converging/diverging nozzle are moved synchronously to maintain the rear edge of the divergent flap portion and the front edge of the veer flap adjacent each other such that the veer flap is aligned with and acts as an extension of the divergent flap portion of the converging/diverging nozzle. Preferably, means are provided to independently trim the orientation of the veer flap to maximize thrust. A movable ventral flap defines the nozzle throat between itself and the deflector hood when the hood is deployed for vertical thrust.

Abstract: A method and apparatus for controlling the direction of the thrust vector of the engine exhaust stream in an upper surface blowing type aircraft includes ducts in the aircraft wings having rotary control valves for controlling the flow of air through the ducts from a source of high pressure to the low pressure upper surface of the wing. Introduction of the airflow at the upper surface rearwardly of the jet engine produces separation of Coanda effect attachment of the engine exhaust stream from the curved upper wing surface. Coanda effect attachment deflects the exhaust stream over the wing and toward the ground and results in a predominantly vertical thrust vector which augments lift of the aircraft. However, separation of the exhaust stream from the upper surface results in a predominantly horizontal thrust vector which augments forward acceleration of the aircraft. The fluidic action of the valves can rapidly change the thrust vector between basically horizontal and highly inclined orientations.

Abstract: A propulsion system for an aircraft having a fuselage and a wing with two nacelles disposed on opposite sides of the fuselage, each of the nacelles having a turbo fan therein with drive means connected thereto for air flow through the nacelle from a forward air inlet to air exit openings, the air flow within the nacelle divided into twi air streams, one of the air-streams being directed downwardly through a variable area forward chin nozzle provided with a cascade of vanes for directing the outflow in a desired direction with the other air stream exhausted through an aft nozzle of variable area at the aft outlet opening against a slotted flap system mounted aft of the aft nozzle against which the outflow from the aft nozzle is directed so that the two air streams provide pitch, roll and yaw control as well as balanced lift and propulsion utilizing controlled thrust modulation and vectoring for all regimes of flight from vertical takeoff and landing (VTOL) or short takeoff and landing (STOL) or a combination o

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 propulsion system for an airplane to permit it to achieve vertical and/or short take-offs and landings. The propulsion system is integrated into a wing/nacelle unit and includes a thrust vectoring system. A separate flow turbofan engine is mounted in each wing/nacelle unit. A system of three flaps is located at the rear of each wing/nacelle unit for deflecting the turbofan engine exhaust downward, rearward, or any angle in between. These three flaps are arranged to provide a main thrust nozzle in the horizontal flight position without any additional flaps between them. One flap is located at the wing/nacelle upper surface trailing edge. Two slots are provided at the leading edge of this flap. The upper forward most slot is provided as an exit nozzle for the engine turbine exhaust, which is shrouded from the fan exhaust. The second of these two slots removes a portion of the high energy fan exhaust from the fan discharge duct and ejects it over a flap upper surface.

Abstract: An airship has a gas-containing annulus contained by the circular base portion of framework the central portion of which extends above the annulus. The capacity of the annulus in accordance with one embodiment is such as to render buoyant a weight equal at least to the major portion of the light ship weight of the airship and in another embodiment, the annulus capacity is such as to render the airship buoyant with a maximum load. The central portion of the framework supports the load lifting propulsion system while the forward propulsion and the guidance systems ride on and are supported by tracks carried by the framework adjacent but above the annulus to travel 90.degree. in either direction from a predetermined straight-ahead position.

Abstract: An inflatable envelope surrounding a compression beam, at least one flexible traction beam associated with the compression beam and surrounding envelope. The traction and compression beams are coplanar and at least one flexible diagonal mechanical network is interposed between the beams integral therewith. The envelope, the compression and traction beams and the diagonal network are connected together so that the inflation of the envelope maintains the assembly of these elements in shape.

Abstract: An aircraft is constructed of an airfoil shaped inflated involucrum of lightweight gas-impervious plastic film. The airfoil is maneuverable to attain forward self-propulsion upon ascent as well as descent. The gases contained in the involucrum are heated by solar radiation to reduce craft density with the upper surface of the airfoil being translucent and the lower surface of the airfoil interior mirrored for concentration of the radiant energy upon an interior cylindrical black spar. A honeycomb reradiation barrier is provided beneath the translucent surface. In one embodiment a large volume involucrum is changeable in camber to maximize forward propulsion. The craft may be utilized to suspend a large fog broom for the purpose of condensation of water vapor. In a further embodiment a manpowered inflatable craft is formed with a flexible longitudinal medial fold which separates the airfoil into wing segments. Each segment includes a passive trailing zone.

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

Abstract: A V.S.T.O.L. gas turbine power plant includes a main gas turbine engine having an exhaust gas propulsion nozzle and a fan arranged within a fan duct, which duct terminates in two nozzles such that a portion of the fan air may be directed vertically downwards or horizontally, the remaining portion of the fan air acts as a working fluid in one or more further auxiliary gas turbine engines each engine including a vectorable exhaust nozzle.

Abstract: A two dimensional vectoring nozzle assembly has an expandable plug therein including a first pair of panels and a second pair of downstream panels extending between spaced, parallel side walls and wherein a pivoted connection between the first pair of inlet panels and the second pair of downstream panels is located at the nozzle throat and is associated with a mechanism to cause the pivoted connection therebetween to move substantially in a vertical plane at the throat of the nozzle between open and closed positions therein and wherein an exhaust port in the nozzle is selectively opened by a movable door operated between open and closed positions by the mechanism and operative when the expandable nozzle is in its closed position to open the door to concurrently restrict flow through the throat region of the nozzle while opening the exhaust port whereby exhaust flow through the nozzle is directed by the blocking action of the expandable plug from a point upstream thereof through the exhaust opening in the nozz

Abstract: Yaw control surfaces are provided for a jet propelled aircraft wherein a thrust augmented rudder is disposed above the jet exhaust stream and a thrust rudder tab extends downward therefrom into the jet exhaust stream with these components being cooperatively deflected to thereby generate yawing moments for directional control of the aircraft.

Abstract: A flow deflector blade primarily for mounting within the efflux of an aircraft propulsion fan so that a change of flow direction can be effected, includes a leading edge member, a trailing edge member, a leaf spring member of arcuate form connecting the two, and filler portions of rubber bonded to each side of the leaf spring member shaped to provide a desired blade contour.

Abstract: A flying disc capable of vertical takeoff, hovering, or powered horizontal flight. The disc includes a discoidal wing that is circular and includes a convex surface on an upper side and a concave lower surface. The wing also includes an inward leading edge that defines a circular opening centered on an upright central axis. The arcuate surfaces converge at the leading edge and at an outer concentric trailing edge. The discoidal wing is freely rotatable on a central support structure that also supports a cockpit. Two sets of turbine blades are affixed to the discoidal wing adjacent the leading edge. Thrust producing engines are mounted to the central support structure to direct thrust radially outward through the turbine blades. This results in rotation of the discoidal wing and produces lift. The angle of thrust may be adjusted such that the thrust is directed only across one or the other set of turbine blades or any selected variation between extreme positions to change the lift characteristics.

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

Abstract: A lift augmenting device to provide a vertical take-off capability in aircraft which includes a pair of rotor assemblies with independently individually pivoted rotor vanes so that the attitude of the vanes can be changed at different positions along the circumferential rotational path of the vanes as they rotate with the rotor assemblies to pump air therethrough and selectively generate lift on the aircraft.

Abstract: The airplane of the present invention is of the vertical take-off and landing type powered by one or more jet engines which are mounted to provide thrust necessary for horizontal flight, movable panels direct exhaust gases downwardly toward the ground to provide a ground effect for greater safety upon vertical take-off and landing.

Abstract: A thrust reverser is provided for use with an asymmetric aircraft gas turbine engine exhaust nozzle. The thrust reverser includes a movable aerodynamic flap downstream of the asymmetric nozzle casing which is rotatable about one pivot in order to effect in-flight thrust vectoring through deflection of the exhaust stream, and which is also independently rotatable about another pivot to effect thrust reversing. In the reverse thrust mode, the leading edge of the flap is immersed into the exhaust stream, thereby splitting the stream into two portions, one of which is deflected upward and forward by a turning vane incorporated into the leading edge of the flap, and the other portion of which is deflected downward and forward by a hinged lip connected to the flap trailing edge. The thrust reverser thus permits the exhaust stream to be ejected in the vertical plane to produce reverse thrust without an accompanying pitch moment even though the exhaust nozzle is not symmetrical in the vertical plane.

Abstract: An aircraft has three propulsion engines, two of which each include one pivotable exhaust nozzle which are arranged one on each side of the aircraft, and a third engine including two pivotable exhaust nozzles, one of which is arranged on either side of the aircraft. The arrangements being such that upon failure of one of the two engines the efflux from the third engine is only directed through the nozzle situated on the side of the aircraft which the failed nozzle is arranged.

Abstract: A rapidly reversible air propeller shroud system is provided for operating an air cushion vehicle more efficiently both in forward and reverse direction travel and maneuvering modes. The shroud includes a sectionally rigid portion of aerodynamically efficient form for operating the vehicle in one direction of travel; and in combination therewith an otherwise inoperative inflatable collar which may be rapidly inflated to expand so as to modify the aerodynamic characteristics of the shroud for operation of the propeller efficiently in reverse direction thrust mode.

Abstract: A STOL aircraft having turbojet or torbofan engines mounted above and forward of the wing whereby the engine exhaust gases flow over and, by the Coanda effect, attach to the upper surfaces of the wing and a downwardly curved extendible flap to produce a downwardly turned exhaust flow having a large vertical component of thrust. Premature separation of the exhaust flow from the wing or flap due to reduced velocity in the boundary layer of the flow, which would result in decreased turning of the exhaust gases and a reduced vertical thrust component, is prevented by a boundary layer scoop extending across the exhaust flow, in an area just prior to where the exhaust flow would separate from the wing or flap, for removing the boundary layer gases and discharging them beneath the wing.

Abstract: The roll control of V/STOL aircraft is augmented by deriving a controlled, transverse thrust component from the lift producing engine. This is accomplished by redirecting a jet to introduce such a component not compensated by a counteracting jet or jet component of the craft. Jets can be redirected through pivoting of bent pipe sections of gimbal-hung nozzles.

Abstract: An air lifting vehicle includes, inter alia, a main frame containing an engine, a helicopter-type rotor driven by the engine, a rear located propeller which provides torque compensation for the rotor as well as yaw control for the vehicle, and a pilot's cabin. Attached to the frame through a plurality of outwardly extending truss members is a keel structure which includes a circular truss section essentially coaxial with and positioned above the rotor and other generally triangular or rounded triangular truss sections attached fore and aft of the circular truss section. Balloon members including fore and aft generally triangular Forlanini envelope sections are secured to the keel and laced together at the center to define a circular opening or duct above the rotor. A pair of forward thrusting propellers are driven by an auxiliary engine carried in the frame and are gimbaled in the elevational plane for pitch control of the vehicle.

Abstract: A composite reinforcement member is provided for reinforcing composite structural joints. The reinforcement member is optimally a laminate of fiber composite sheets of uniform size and shape which are adhesively bonded together. By virtue of the shape of the laminate and arrangement of the sheets, the fibers substantially distribute a tension load to minimize peel forces on the structural joint.

Abstract: Lighter-than-air apparatus includes a thin, pliable air-tight outer envelope disposed in overlying relationship over a light-weight, coarse-opening inner frame of a spherelike shape. The envelope includes a sealable opening therein, so that the envelope can be at least partially evacuated to render the apparatus lighter than air. A vacuum pump is provided and is connected in fluid communication with the opening for controlling the quantity of air contained in the envelope to determine the amount of lifting energy. In one form of the invention, an outer frame is disposed within the envelope and surrounding the inner frame, and the outer frame is composed of a stiff, rigid open-mesh material with the openings in the inner frame being smaller in size than the opening in the outer frame.

Abstract: A variable lift inflatable airfoil for tethered balloons having a horizontal fin made up of two inflatable chambers. The primary or lower chamber is normally maintained at a greater pressure than the secondary or upper chamber. Proper inflation and deflation of the secondary chamber will stabilize the pitch attitude of the balloon at some desirable low, positive angle for any wind velocity.

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

Abstract: A wingless vertical take-off aircraft having multiple ducted propeller rotors with controllable pitch blades symmetrically mounted in the forward and the rear portions and on both sides of the aircraft with the ducts angled downwardly at an acute angle to the aircraft longitudinal axis, transversely extending deflector vanes pivotable vertically within the exit portion of the ducts, and a rudder for yaw control mounted in the exit portion of each rearwardly located duct. Control in altitude and in attitude about the pitch and roll axes is achieved by controlling the collective pitch of the propellers in selected ducts with the roll control being interconnected to the yaw control to counteract roll/yaw coupling effects and control in trim and forward flight thrust being provided by setting the position of the deflector vane to divert the air flow from the ducts in variable directions with respect to the aircraft axis and the vertical.

Abstract: The disclosed semi-buoyant lift-augmented aircraft, preferably of immense size, includes a fuselage of airfoil shape formed by a rigid geodesic type web framework enclosing buoyant cells pressurized to reinforce the framework. Wings are provided which impart aerodynamic lift to the aircraft, with the airfoil fuselage. The buoyancy is provided to counteract a major proportion of the great weight of the structure and to thus improve the aircraft's payload capability and range. These features maintain it airborne at reasonable speeds over a substantial altitude range.

Abstract: A nozzle assembly for use with a jet engine for controlling the direction of the discharged fluid and hence the direction of thrust is disclosed. The nozzle housing and an internally mounted bifurcation structure are arranged to divide the exhaust fluid flowing into a circular entrance orifice into two separate fluid streams that flow out of rectangular discharge orifices on the rear face of the nozzle. Flow deflection doors, stored within a rearwardly opening cavity formed by the bifurcation structure between the two rectangular discharge orifices, are selectively extendable into each fluid stream to modify the direction of the discharged fluid. The two flow ducts formed by the bifurcation structure and nozzle housing are configured to discharge the two fluid streams toward one another such that the fluid streams converge into a single, thrust-producing fluid stream aft of the exit orifices when the flow deflection doors are not deployed.

Abstract: Aerostats and aquastats are described in which a sealed envelope of flexible material impervious to the passage of gas therethrough is mounted on a flexible frame forming a permanent part of the device and which can be caused to expand the envelope after it has been wholly or very substantially evacuated of internal gas, thereby setting up a vacuum or partial vacuum condition in the envelope. In the case of a partial vacuum, the gas at reduced pressure may be hydrogen or helium. The lift or buoyancy of the device may be controlled when in use by altering the volume of the envelope by adjusting the shape of the frame by acting mechanism carried by the device. The frame may comprise flexible rods connected together at opposite ends so that by forcing the opposite ends of the rods towards one another they are bowed outwards distending the envelope towards a globular form.

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

Abstract: An aircraft for making vertical and short field takeoffs is powered by a ass turbofan engine having a core turbojet and a bypass fan. For vertical takeoffs, the efflux from the bypass fan is deflected downward to create lift. Exhaust from the core turbojet is ducted to turbine driven lifting fans at remote locations to create supplemental lifting forces which also provide aircraft control and stability. For cruise, the bypass fan efflux is discharged aft until sufficient forward airspeed is attained that exhaust gas flow to the lifting fans may be shut off, and exhaust gas flow may also be discharged aft.

Abstract: A variable density aircraft is formed of at least one variable volume container such as a balloon, gas cell, or collapsible hinged panel hull which is supplied with a gas for container expansion and comtraction by an aircraft carried reversible, fluid expansion/contraction system. The variation of the volume of such containment device without a commensurate variation of mass results in a densemetric variation in the aircraft.

Abstract: A lighter than air ship, with a bow plate on the bow, two cars suspended beneath the elongated bag, the cars having water ballast tanks, with scoops to take in water when the airship is landing on water and valves to let the water out when the airship is taking off, with a sea anchor and rode (rope) to the bow plate, a ground (bottom) anchor and rode (rope) to the bow plate, metal ribs attached to the bow plate and extending to a stern plate and connected to the bag both above and below the bag, with a vertical rudder for steering right and left, horizontal rudders for steering up and down and a ballonet inside the bag for keeping proper pressure, landing wheels for landing the airship on land, the cars being capable of landing the airship on water, the bag having an aerodynamic lifting shape so that the airship can take off and fly heavy and by dumping water can land safey and landing on water can take in water to be stable on the surface, can land on land with the wheels and be secured by the rodes.

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