Abstract: An aircraft has a fuselage designed essentially as an aerostatic lift body. Combined lift and propulsion devices are articulated on the fuselage, are provided with propellers and form propulsion units and which in each case can tilt between a lift position, in which the respective propeller rotation plane is essentially horizontal and a propulsion position, in which the respective propeller rotation plane is essentially vertical. Additionally the propeller rotation plane has all-round inclination relative to the output shaft of the associated drive device.

Abstract: The convertible aircraft with tilting rotors comprises two fixed wings with zero sweep on which an inter-connecting shaft is substantially rectilinear and parallel with the pivot axis but offset from this axis, substantially perpendicular to a longitudinal axis of symmetry of the aircraft, the center of gravity of which, in helicopter mode, is substantially in a vertical plane passing through the pivot axis and, in aeroplane mode, is substantially contained in or is in proximity to another vertical plane passing through the straight line of the aerodynamic centers of the wings.

Abstract: To provide aerodynamic continuity between the front part, pivoting with the rotor, and the stationary rear part of a pod housing an engine for driving the rotor, a curved cowl curved about the pivot axis extends the rear edge of the bottom cowling of the front part to join this rear edge to the front edge of a bottom cowling of the stationary rear part, in helicopter mode, and a flap swivel-mounted on the top cowling of the front part joins this latter to the top cowling of the stationary rear part, onto which this flap is folded, in helicopter mode.

Abstract: The aircraft comprises a central cabin, which is located in the center of a circular wing. Several pivotal electric drive units are arranged in a gap between the central cabin and the circular ring. In hover flight, the drive units are pivoted to generate a lift. When the aircraft goes into cruise flight, the drive units are pivoted to generate a forward thrust. Attitude and movements of the aircraft can be controlled by individual or common adjustment of the thrust and pivot angle of the drive units. Due to its simple design, the aircraft is economic and safe in operation. Still it has a high payload for its size.

Abstract: A pylon conversion system (100) for operating a pylon (12) on a tiltrotor aircraft (10) between an aircraft mode and a helicopter mode is disclosed. The system (100) comprises first and second pylon conversion actuators (102,104) each having a retracted position and an extended position which corresponding to the aircraft mode and the helicopter mode. A first gearing system (156) is operably coupled to the first pylon conversion actuator (102) and to a first primary power unit (110), a first backup power unit (112) and a first clutch (138). A second gearing system (158) is operably coupled to the second pylon conversion actuator (104) and to a second primary power unit (114), a second backup power unit (116) and a second clutch (142). An interconnect drive train (126) is operably coupled to the first and second clutches (138, 142) such that the first and second pylon conversion actuators (102, 104) are operable between the extended position and the retracted position.

Abstract: A vehicle that combines the freedom and swiftness of flight with the utility of surface travel. A simple, light weight, safe and stable conveyance with positive yaw-roll coupling, special safety features, no fold wing stowage and a unique single power source. It can be built using common tools and techniques with readily available materials at a cost competitive with the family automobile.

Abstract: A tiltrotor aircraft includes a spanwise-flow redirector having a pair of flow-redirection panels respectively mounted on the aircraft's mid-fuselage area for rotation about a panel pivot axis between a stowed position and a deployed position. In the stowed position, each panel is substantially flush with an adjacent surface of the mid-fuselage area. In the deployed position, each panel is raised into the path of one of the inbound spanwise flows generated by the aircraft's rotors during hover operation, whereupon each panel redirects the respective one of the inbound spanwise flows either forward or aft of the other inbound spanwise flow. In this manner, the deployed panels prevent stagnation of the inbound spanwise flow atop the mid-fuselage area while further serving to minimize re-ingestion of merged spanwise flow into the rotors, resulting in decreased airframe download forces, increased rotor thrust, and reduced noise levels during hover operation.

Abstract: The device for lift and to reduce forward resistance of aircraft consists of a converging input duct of truncated-cone-shaped or truncated-pyramid-shaped, arranged lengthwise inside the fuselage and inclined to the longitudinal axis, with the larger opening coinciding with the front fuselage contour or periphery of maximum cross-section, and reducing in bore backwards so that its generatrix or lower side coincides with the lower surface of the fuselage parallel to the aircraft's longitudinal axis and the generatrix or upper edge forms an acute angle with the aircraft's longitudinal axis. The narrowest end of the duct discharges into the input of the turbofan, UHD, etc. type drive engines which discharge through a rear outlet duct facing backwards with the rear end curved slightly downward.

Abstract: A method and arrangement for propelling fluidborne vehicles is disclosed that results in reduction in the overall form drag of certain classes of vehicles. The method and arrangement consists of using a propulsion system with an inlet that circumscribes the transition region between a forebody section containing the widest part of the vehicle and a tapered afterbody section of the vehicle to remove fluid from the viscous boundary layer that is generated by the forward portion of the vehicle, and accelerates this boundary layer fluid through a propulsion system in the afterbody portion of the vehicle. Removal of boundary layer fluid can reduce momentum losses which occur in the wake created by various classes of vehicles.

Abstract: A drive system for a variable diameter rotor system that includes a plurality of rotor blade assemblies with inner and outer blade segments. The outer blade segment being telescopically mounted to the inner blade segment. The drive system engaging a jackscrew for telescoping the outer blade segment with respect to the inner blade segment. The drive system includes a rotor hub that is pivotally mounted to the upper end of a main rotor shaft about a pivot point. A gimbaled bearing is disposed between and attached to the main rotor shaft and the rotor hub. The gimbaled bearing permits the rotor hub to pivot about the pivot point. A blade actuation shaft is concentrically disposed within the main rotor shaft. The blade actuation shaft has a constant velocity joint pivotally attached to its upper end about the pivot point. A planetary gearset engages the blade actuation shaft with the jackscrew.

Abstract: A rotor blade actuation system is disclosed for controlling extension and retraction of an outboard blade section of a rotor blade by varying the speed and direction of rotation between a main rotor shaft and a blade actuation shaft. The rotor blade actuation system includes a drive gear on the main rotor shaft and a blade actuation drive gear on the blade actuation drive shaft. A primary drive unit is engaged with and transmits rotary motion from the main rotor shaft to the blade actuation shaft. The primary drive unit includes an input gear engaged with the drive gear. A primary drive is engaged with the drive gear through an input gear and a master clutch. An output drive is engaged with the blade actuation drive gear. A forward clutch controls engagement of a forward planetary gearset with the primary drive and the output drive. The engagement of the forward planetary gearset causes the blade actuation shaft to rotate in the same direction as the rotation of the main rotor shaft.

Abstract: There is disclosed an angle positioning platform for positioning objects around first and second axes and a gearbox for same. The platform comprises a base, an intermediate stage, and an upper stage. The platform may have motors and first and second output gearboxes connected to the motors for driving the platform. The orientation of the stages of the platform permits the platform to be relatively compact in a stowed position and to have high angular rotation from the stowed position to a maximum travel position. The gearboxes may have a mechanism for isolating worm shafts and wormgears from heavy loads when the platform is in the stowed position. Another aspect of the invention is an output gearbox with a wormgear having stops for stopping rotation of a matingly engaged worm. Another aspect of the invention is a gearbox having torsion springs to counter backlash in the gearbox.

Abstract: Rotor blade stowing system for stowing rotor blades that conserves storage space without adding significant weight or cost to the aircraft. The system includes a rotary actuator disposed on a blade grip member. A rotor blade is pivotally connected to the blade grip member. The rotary actuator is operably coupled to a blade pivoting cam and a locking cam. The system includes a cam follower linkage which has a first end which includes a blade pivoting cam follower and a locking cam follower and a second end. The blade pivoting cam follower follows the blade pivoting cam. The locking cam follower follows the locking cam. The second end of the cam follower linkage is coupled to the blade grip member. The system includes a shaft rotatably coupled to the blade grip member, a locking linkage bell crank operably coupled to the shaft, a delay cam coupled to the blade grip member, and a locking linkage idler operably coupled to the locking linkage bell crank.

Abstract: A vertical takeoff and landing aircraft has a fuselage with a wing located above the fuselage at the rearward end and with a horizontal stabilizer located at the forward end. The propellers are mounted on booms separate from the wings and located just behind the center of gravity of the aircraft. The propellers are pivotable between horizontal and vertical axes and brakes are provided to allow locking of propeller position. When the brakes are released, the propellers automatically pivot between vertical and horizontal orientations and vice-versa based upon control of the aircraft by the pilot.

Abstract: The vehicle includes a fuselage; a plurality of lifting surfaces attached to the fuselage having control devices attached thereto; and, an articulated propulsion system attached to the fuselage. The propulsion system includes a duct assembly pivotally connected to the fuselage. The duct assembly includes a duct and a propeller assembly mounted within the duct. A motor assembly is connected to the propeller assembly. The duct assembly may be positioned in a substantially vertical position to provide sufficient direct vertical thrust for vertical take-off and landing and may be directed in other positions to provide a varying spectrum of take-off and landing configurations, as well as a substantially horizontal position for high speed horizontal flight. Use of the control surface in the ducted propulsion assembly provides VTOL capability in a very small environment. The environment is not required to be prepared in any special manner.

Abstract: The invention relates to a tiltrotor helicopter comprising a fuselage (1), a wing arrangement (2) and at least one power plant (5), and including two contrarotating, cyclically controllable rotors (7, 8) which are spaced from one another in the longitudinal direction of the fuselage and arranged substantially on a longitudinal axis of the fuselage (1) as well as being respectively tiltable out of a first tilted position for helicopter flight into a second tilted position for airplane flight, the first rotor (7) being arranged at the front end of the fuselage (1) and substantially above the same and the second rotor (8) being arranged at the rear end of the fuselage (1) and substantially beneath the same, and the first rotor (7) being tiltable about a tilting axis (17) extending substantially perpendicularly to the longitudinal axis of the fuselage (1) out of the first tilted position downwardly and in front of the fuselage (1) into the second tilting position and the second rotor (8) being tiltable about a ti

Abstract: Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.

Abstract: The thrust director assembly may include a thrust director cone with its apex oriented into the fan airstream and a larger thrust vectoring ring concentric with the director cone. The thrust director assembly axis is angularly displaceable relative to the fan axis for modifying the geometry of the duct outlet such that the aperture of the outlet annulus is reduced on one side and simultaneously enlarged at a diametrically opposite side. The effect of the modified geometry is to increase fan thrust on the enlarged side while diminishing thrust on the narrowed side, thereby to develop a lateral thrust component acting on the airframe for providing long moment pitch and roll control.

Abstract: The difficulty and expense of fabricating a support strut for a ram air driven turbine are reduced by providing an axially opening channel in a central portion of the strut. Blockage of a portion of the airstream flowing through the ram air turbine and past the strut is reduced by extending the axially opening channel through the entire axial length of the strut. Apparatus for converting or transferring power generated by the ram air turbine to a point of use, such as an aircraft, is routed through the axially opening channel, thereby allowing convenient access to such apparatus. A strut design is provided which may be readily manufactured as a single unitary structure from a variety of metallic and non-metallic materials including fiber reinforced composites.

Abstract: In a vertical take-off and landing vehicle, the invention is a method for improving stability by virtue of establishing conversion of thrust vectors over the center of gravity of the vehicle while in the hover position. Through the use of selected angles of inclination of the thrust-generating devices, a positive static stability of the aircraft is maintained. In addition, the spars supporting the thrust-generating devices are mounted in a fixed angular relationship to the centerline of the aircraft's fuselage, to achieve the desired inclination of the thrust vectors of the lift-generating devices toward the centerline of the vehicle, by simple rotation of the spars on which the lift-generating devices are mounted.

Abstract: A tilt wing VTOL aircraft has a fuselage with sides and an upper surface, an upper wing having a leading edge, a trailing edge, a chord, a lower surface and an upper surface. The wing is pivotally mounted on the fuselage for rotation from a cruise flight position in which the upper surface of the wing is flush with the upper surface of the fuselage to a hover position in which the wing is perpendicular to the upper surface of the fuselage. Aircraft engines are mounted on the wing. The aircraft has a pair of flaps at the trailing edge of the wing, each located between the fuselage and an engine and each spaced the same distance from the fuselage and each of the engines. The flaps are mounted for selective movement from colinearity with the chord of the wing to a first angle of about +30.degree. with the chord and about 30.degree. with the upper surface of the wing and to a second angle of about -30.degree. with the chord and about 30.degree. with the lower surface of the wing.

Abstract: An omnidirectional propelling type of airship can be propelled in any direction in three-dimensions. The airship includes an airtight gas chamber, gas having a specific gravity smaller than that of air and filling the gas chamber, a section capable of accommodating men, cargo and the like, and propellers supported by gimbals and capable of propelling the airship in any spacial direction.

Abstract: A tiltwing aircraft, capable of in-flight conversion between a hover and forward cruise mode, employs a counter-rotating proprotor arrangement which permits a significantly increased cruise efficiency without sacrificing either the size of the conversion envelope or the wing efficiency. A benefit in hover is also provided because of the lower effective disk loading for the counter-rotating proprotor, as opposed to a single rotation proprotor of the same diameter. At least one proprotor is provided on each wing section, preferably mounted on the wingtip, with each proprotor having two counter-rotating blade rows. Each blade row has a plurality of blades which are relatively stiff-in-plane and are mounted such that cyclic pitch adjustments may be made for hover control during flight.

Abstract: An unmanned aerial vehicle incorporates a single engine with bifurcated exhausts which are coupled to side mounted rotating nozzles through a swivel joint. Jet deflection means are mounted to the end of the rotating nozzles to achieve additional degrees of freedom for the aircraft.

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: An amphibious aircraft capable of V-STOL operations, the aircraft comprised of a pair of buoyant, coterminus, and elongated body members having an axially converging and diverging profile, joined together at the forward end thereof by a forward fuselage having at least one cambered surface, the entire structure thereof functioning as a lifting body, the forward fuselage having a pair of wings rigidly attachable thereto, and at least one propulsion unit attachable thereto proximal to the aircraft's longitudinal centerline, whereby the transition between vertical and conventional flight modes may be accomplished, the aircraft further having a stabilizer for pitch and yaw control which are pivotally and hingedly attachable to the rear of said elongated body members.

Abstract: A latch pin and locking system for use in connection with an aircraft having folding wings or wing tips. The system includes a plurality of individual latch pin units, each of which has a pin that is hydraulically driven in extension and retraction. When extended, the pins cooperatively lock wing tip hinge structure which prevents wing tip folding movement. Each latch pin unit has a locking body that prevents pin retraction of its respective pin after extension thereof for wing tip locking. The locking bodies of all of the latch pin units are drivingly interlinked, so that all lock and/or unlock as a single network. The network is driven by a single power drive unit. In the event any one locking body in the network fails, the network is broken, and thereby provides an indication that maintenance is required.

Abstract: A tilt wing VTOL aircraft has an upper wing with a leading edge, a trailing edge, an inboard area adjacent the fuselage, spaced opposite end tip areas and an upper surface. The wing is pivotally mounted on the fuselage for rotation from a cruise position in which the upper surface of the wing is flush with the upper surface of the fuselage to a hover position in which the wing is perpendicular to the upper surface of the fuselage. The wing has a forward portion in the leading edge of the inboard area affixed to the fuselage and cut out of the wing and an aft portion in the trailing edge of the inboard area affixed to the fuselage and cut out of the wing.

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

Abstract: The invention concerns an aircraft with engine pods located outboard on the wings and tiltable about a transverse axis. A fixed wing centerpiece is provided which terminates at the outside in each spanwise direction in a separation location. A through tubular spar is rotatably supported in the wing centerpiece. This tubular spar serves as a support for the outer wings which continue beyond the separation locations and which, together with the engine pods located there, form a unit which can be jointly swivelled or tilted.

Abstract: A drive system for a tiltrotor aircraft that provides for the operation of both proprotors by either engine or by both engines. The drive system provides an interconnecting drive shaft that extends between and connects the engines in such a manner that power is transferred from one engine to the opposite proprotor in the case of an engine failure. Also, the arrangement provides for the operation of a redundant essential systems for the aircraft should an electrical or hydraulic system fail to operate properly.

Abstract: An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft. The pipe structure can be pivoted in respective bearings to effect the pivotal movement of the propellers and wing portions for either vertical take off and landing or for horizontal flight. The pipe structure is built by pipes without bends in order to make the cleaning of the interiors of the pipes from dirt and from remainders of welding possible.

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: An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft.The pipe structure can be pivoted in respective bearings to effect the pivotal movement of the propellers and wing portions for either vertical take off and landing or horizontal flight. The pipe structure is built by pipes without bends in order to make the cleaning of the interiors of the pipes from dirt and remainders of weldings possible. Ribs and holding portions are provided on the structure for assembly and/or disassembly of the wing portions to the pipe structure.

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 remote control lighter-than-air toy apparatus has an inflatable container having a predetermined shape, such as the shape of a dirigible, for holding a lighter-than-air gas. A gondola is removably attached to the inflatable container and has a shaft extending therethrough and rotatably supported thereon. A reversible electric motor is attached to each end portion of the shaft passing through the gondola with each electric motor having a propeller attached thereto for rotation upon actuation of the electric motor. Each of the electric motors and propellers are rotatably attached to the shaft. A radio receiver is connected to each of the electric motors with a plurality of conductors. A control box has a radio transmitter therein and a plurality of controls thereon for transmitting to said receiver and remotely controlling each motor separately, so that a lighter than air toy can be remotely controlled with two propellers.

Abstract: An airborne craft with at least four propellers arranged in a front propeller pair and a rear propeller pair having substantial vertical or forwardly inclined axes has hydraulic motors which drive the propellers. A pumping device supplies two pairs of separated flows to the motors. One pair of the flows has fixed delivery and equal flow quantities per revolution of the pump while the other pair has variable flow-rates but the flow quantities of both flows of the variable flow pair are also equal relatively to each other. One of the flow pairs drives the front propellers at equal speeds and the other pair of flows drives the rear propellers with equal speeds. But the variability of the rates of flow of one of the pairs of flows is utilized to let one of the pairs run with a different rotary velocity of the propellers than the other pair.

Abstract: An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft.The pipe structure can be pivoted in respective bearings to effect the pivotal movement of the propellers and wing portions for either vertical take off and landing or horizontal flight. The pipe structure is built by pipes without bends in order to make the cleaning of the interiors of the pipes from dirt and remainders of weldings possible. Ribs and holding portions are provided on the structure for assembly and/or disassembly of the wing portions to the pipe structure.

Abstract: In a vehicle or device a fluid motor is employed to drive rotary members, such as wheels, propellers, tracks. The motor is provided with an arrangement which includes a control means and an axially moveable member. By utilizing the control means, for example, by a flow of fluid, the axially moveable member is used to apply an action, which is not common to the usual operation of fluid motors. The arrangement may be used to arrest the rotor of the motor from rotation when no pressure is in the driving fluid line. It may also be used to control the pitch of propellers with variable pitch arrangements. Also possible is to use the arrangement to automatically obtain an auto - rotation of rotor blades on vertical axes of vertically take off and landing vehicles, when the pressure in the fluid line to the motors for driving the motors drops below a predetermined minimum of pressure.

Abstract: An aircraft has a pair of wing portions with propellers of a propeller pair which are driven and synchronized by a fluid transmission between the power plant and the propellers. A fluid line structure keeps most components of the craft together and consists preferredly of three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The take over of a plurality of functions by the interior pipe structure reduces weight and secures safe and economic operation of the craft. In the type of the aircraft where this application deals with, a variable pitch propeller may be applied which operates with variable pitch at flight to obtain its best efficiency at the respective speed of flight while the propeller is set with its chord parallel to the chord of the wing or tail when it is retracted into a slot in the wing or tail when another propeller drives the craft forward in leveled flight.

Abstract: The invention relates to a rigid wing flying craft having at least one airfoil and at least one driving unit and a cabin for receiving loads. At least one air channel piercing the airfoil is provided in the surface center of the airfoil and at least two steering fins for steering the flight movements are pivotably supported in the air channel. The driving unit and the steering fins are arranged at least partially within said air channel and pivotably supported within the same around an axis of rotation which extends essentially vertically in relation to the axis of the driving unit.

Abstract: Propellers are provided to drive a vehicle or to bear a vehicle in air. Such propellers have commonly been fixed to wings or fuselages. The fixed locations of the propellers limited the abilities and capabilities of the respective vehicle. The invention now provides arrangements on or to propellers which makes it possible to change the location of the respective propeller relatively to another portion of the vehicle. The change of the location of the propeller in relation to another portion of the vehicle makes it possible to improve the abilities or capabilities of the vehicle. Specifically beneficial effects are obtained by applying the invention to propeller-pairs. Specific relations of locations of propellers to wings or to flow of air in combination with means to pivot portions of the arrangement(s) can lead to better overall efficiencies, speeds, bearing capacities, economy or comfort of the vehicle or of portions thereof.

Abstract: An aircraft capable of vertical short takeoff and landing is shown according to the teachings of the present invention as including four separate engine locations. In its most preferred form, the first and second engines are located on opposite sides of the fuselage of the aircraft and are pivotal about first and second axes which are in a plane perpendicular to the longitudinal axis of the aircraft and which are in front of the center of gravity of the aircraft. The third and fourth engines are located on opposite sides of the fuselage of the aircraft and are pivotal about third and fourth pivot axes which are parallel to the first and second axes of the first and second engines, respectively, but which are behind the center of gravity of the aircraft. The engines are mounted and rotated about their respective pivot axes by a system including a shaft having a first end operatively attached to the engine.

Abstract: A short takeoff and landing aircraft (10) and vertical/short takeoff and landing aircraft (10), having upper surface blowing engines (12, 14) on gull-shaped wings (24, 26) which may be tilted and translated by a variable incidence translation device (52). The translation means (80, 62, 64) is adapted to provide center of gravity travel trim and critical engine out moment trim. Thrust vectoring of the upper surface blowing engines is accomplished by a combination of the upper surface blowing and wing tilt, and vectoring of lower lift/boost engines (124, 126) is accomplished by swiveling nozzles (138, 140). Critical engine out lateral trim is accomplished by a combination of airplane bank and differential vectoring by the lower lift/boost engines (124, 126).

Abstract: A wingless aircraft that has a generally truncated cone fuselage that has a cockpit in the upper thereof in which the pilot sits, and a transparent rigid dome mounted on the upper portion of the fuselage that extends over the pilot. A number of equally spaced, elongate, jet engine assemblies are pivotally and adjustably supported within the fuselage, with each engine in communication with an air inlet defined in the fuselage. Each jet engine assembly includes a combustion chamber that has an elongate tubular nozzle extending downwardly therefrom, in which exhaust openings are defined through which the hot gaseous products of combustion discharge. The exhaust openings are elongate and substantially angularly disposed relative to the vertical, and as a result the exhaust gases not only rotate the nozzle but exert a reactive force sufficient to lift the fuselage to an airborne position.

Abstract: An aircraft has a pair of tiltable wings for vertical and horizontal flight with propeller-pairs which are driven and synchronized by a fluid transmission between the power plant and the propellers. The interior structure which keeps most of the components of the craft together consists of at least three pipes which are also utilized to carry the driving fluid to and from the motors, to hold the motors and to hold the wings. The pipe structure can be pivoted in respective bearing means of the body of the aircraft to effect the pivotion of the propellers and wings for either vertical take off and landing or for horizontal flight. The take over of a plurality of functions by the interior pipe structure reduces weight and assures safe and economic operation of the craft.

Abstract: A VTOL airplane having a stub wing integrating a powerplant to either side of an airplane fuselage to rotatably relate the powerplant means to the airplane fuselage for uniform rotation, allow for flexible interconnecting design and lower the use of gravitational and aerodynamic moments in assistance of rotation of this powerplant/stub wing assembly.

Abstract: A method of and apparatus for anchoring an airship containing lighter-than-air gas includes positioning one or more magnets, flush with the edges of a support member attached to the airship for enabling the magnet to contact a magnetically attractive anchoring structure affixed to the ground when anchoring is desired, and, when ascent is desired, bearing against the anchoring structure with the support member to separate the magnet from the anchoring structure. The support structure may comprise a hollow shaft attached to a downwardly-facing portion of the airship, with a relatively large area base portion at its other end, having a cavity formed in the bottom of the base portion in communication with the hollow portion of the shaft. The magnet is coupled to a lifting device which bears against the top end of the shaft to control the magnet's position in the cavity.

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: A lift and propulsion system for partial piloting of a pendular effect piloted aircraft having a gliding structure. The system comprises a frame having a frame axis which is parallel to the pitch axis of the aircraft, the frame being rotatable about the frame axis. A pair of engines are supported by the frame and are each provided with throttle valves for controlling the power or speed of such engines. A rotation control lever arm having one end connected to the frame and the other end movably connected to the gliding structure is provided for controlling the rotation of the frame about the frame axis to control the orientation of the thrust of the engines, and a throttle control mechanism is provided for simultaneously and differentially controlling the power of the engines. The throttle control mechanism comprises a handle having a longitudinal axis and a support member for supporting the handle for rotation about such longitudinal axis.