VTLH autogyro

Claim 2

A lift rotor assembly adapted to be gimbal mounted in relation to the fusilage body of an autogyro for the purpose of enlarging its performance capability to include hovering and vertical ascent and descent comprising, in combination: an upper rigid circular disc structure having a flattened dome-like profile and closed by a flat disc, a lower rigid circular disc structure having a flattened dome-like profile and closed by a second flat disc, a first set of blades uniformly distributed about and secured to the periphery of said upper disc structure, a second set of blades uniformly distributed about and secured to the periphery of said lower disc structure, both sets of blades being wind-driven, and means for mounting and gearing together said disc structures for counter-rotation on a common axis, with the structures in mirror image relation and the discs so close together that the two structures cooperatively form an airfoil with auto-gyrating capability.

Claim 3

An autogyro formed with a fuselage body and having vertical ascent, hovering and descent capabilities along with conventional flying and take-off capabilities comprising, in combination: a pair of rigid, circular lift disc structures, one upper and one lower, mounted so close as to perform as a single aerodynamic lifting body, individual sets of blades uniformly distributed around and secured to the respective peripheries of said disc structures, disc mounting means including a single shaft for mounting and gearing together said disc structures for counter-rotation, a gimbal mounting secured to said shaft and a mast secured to said body for providing two degrees of controlled rotational freedom between fuselage and the assembly of disc structures and their mounting means, means for coupling said lower disc structure to a drive train, this drive train including a first clutch of the type which disengages when unloaded or at the command of and operator, the drive train further including a second clutch for selectively engaging and disengaging the power train from a power supply means, power supply means coupled to said drive train, forward flight-propulsion means, adjustable to provide a range of thrust, a coupling between the power-supply means and said flight-propulsion means.

Claim 4

An autogyro formed with a fuselage body and having vertical ascent, hovering and descent capabilities along with conventional flying and take-off capabilities comprising, in combination: a pair of rigid, circular lift disc structures, one upper and one lower, mounted so close as to perform as a single aerodynamic lifting body, individual sets of blades uniformly distributed around and secured to the respective peripheries of said disc structures, disc mounting means including a single shaft for mounting and gearing together said disc structures for counter-rotation, a gimbal mounting secured to said shaft and a mast secured to said body for providing two degrees of controlled rotational freedom between fuselage and the assembly of disc structures and their mounting means, means for coupling said lower disc structure to a drive train, this drive train including a first clutch of the type which disengages when unloaded or at the command of and operator, the drive train further including a second clutch for selectively engaging and disengaging the power train from a power supply means, power supply means coupled to said drive train, forward flight-propulsion means, adjustable to provide a range of thrust, a coupling between the power-supply means and said flight-propulsion means.

Claim 5

An autogyro according to claim 2 in whch the gimbal mounting comprises; a roller having a longitudinal axis fore and aft and secured to said shaft to permit controlled roll between body and the disc structure assembly including said shaft, and a pitch box providing a journal for said roller, said box having an axis transverse to said body and means for mounting said pitch box on said mast for controlled rotation about said transverse axis to permit controlled pitch between body and the disc structure assembly.

Claim 6

In an autogyro having a fusilage, a novel airfoil assembly spaced from the fusilage and comprising, in combination: a rigid upper plano-convex rotor structure, circular in plan, a rigid lower plano-convex rotor structure, circular in plan, each of said rotor structures having wind-driven peripheral blades short in length compared to the diameter of said structures, and means for mounting and gearing together said structures for counter-rotation on a common axis in mirror image relation and with the adjacent flat surfaces of the structures so closely spaced that the remote convex surfaces provide a single airfoil with auto-gyrating capability.

Claim 7

In an autogyro having a fusilage, a novel airfoil assembly spaced from the fusilage and comprising, in combination: a rigid upper plano-convex rotor structure, circular in plan, a rigid lower plano-convex rotor structure, circular in plan, each of said rotor structures having wind-driven peripheral blades short in length compared to the diameter of said structures, and means for mounting and gearing together said structures for counter-rotation on a common axis in mirror image relation and with the adjacent flat surfaces of the structures so closely spaced that the remote convex surfaces provide a single airfoil with auto-gyrating capability.

Claim 8

In an autogyro, the combination of: a fusilage body, a rotor pair comprising two rigid circular structures each profiled with a a flat face and a convex airfoil surface, peripheral blade sets on said structures, said structures being disposed with their faces so close together that their convex surfaces form a single aerodynamic wing, means for mounting and gearing said rotor pair for counter-rotation on a common axis, gimbal means securing said mounting means to said body, and means in said body for controlling the tilt of said rotor pair relative to said body.

Claim 9

In an autogyro, the combination of: a fusilage body, a rotor pair comprising two rigid circular structures each profiled with a a flat face and a convex airfoil surface, peripheral blade sets on said structures, said structures being disposed with their faces so close together that their convex surfaces form a single aerodynamic wing, means for mounting and gearing said rotor pair for counter-rotation on a common axis, gimbal means securing said mounting means to said body, and means in said body for controlling the tilt of said rotor pair relative to said body.

Claim 10

In an autogyro of the type including a fusilage body, gimbal connector, forward-flight propulsion means, and rotor-tilt control means, an improved rotor assembly distinct from the body comprising, in combination: upper and lower rigid circular blade-bearing rotor structures profiled and positioned to have closely spaced inner faces and curved outer faces, and means secured to the connector for mounting and gearing the rotor structures together on a common axis so that the curved surfaces comprise a single airfoil, the curved surfaces being continuous except as the mounting means requires interruption.

Claim 11

In an autogyro of the type including a fusilage body, gimbal connector, forward-flight propulsion means, and rotor-tilt control means, an improved rotor assembly distinct from the body comprising, in combination: upper and lower rigid circular blade-bearing rotor structures profiled and positioned to have closely spaced inner faces and curved outer faces, and means secured to the connector for mounting and gearing the rotor structures together on a common axis so that the curved surfaces comprise a single airfoil, the curved surfaces being continuous except as the mounting means requires interruption.

Claim 12

In an aircraft having a body and with the capability of auto-gyrating, a rotor assembly distinct from the body comprising, in combination: a pair of structurally rigid circular rotors each bearing peripheral wind-driven blade elements, the rotors being formed with conforming inner faces and curved outer surfaces, and means mounting and gearing said rotors for counter-rotation on a common axis with the conforming faces spaced so closely together that the curved surfaces form a single airfoil, the curved surfaces being continuous except as the mounting means requires interruption.

Claim 13

In an aircraft having a body and with the capability of auto-gyrating, a rotor assembly distinct from the body comprising, in combination: a pair of structurally rigid circular rotors each bearing peripheral wind-driven blade elements, the rotors being formed with conforming inner faces and curved outer surfaces, and means mounting and gearing said rotors for counter-rotation on a common axis with the conforming faces spaced so closely together that the curved surfaces form a single airfoil, the curved surfaces being continuous except as the mounting means requires interruption.

Claim 14

In an aircraft having a body and with the capability of auto-gyrating, the combination of: forward flight propulsion means, and a rotor assembly distinct from the body comprising a pair of structurally rigid circular rotors each having wind-driven blade elements projecting from its periphery, the rotors being formed with conforming inner faces and curved outer surfaces, and means mounting and gearing said rotors for counter-rotation on a common axis with the conforming faces so close together that the curved surfaces provide a single airfoil, the curved surfaces being continuous except as the mounting means requires interruption.

Claim 15

In an aircraft having a body and with the capability of auto-gyrating, the combination of: forward flight propulsion means, and a rotor assembly distinct from the body comprising a pair of structurally rigid circular rotors each having wind-driven blade elements projecting from its periphery, the rotors being formed with conforming inner faces and curved outer surfaces, and means mounting and gearing said rotors for counter-rotation on a common axis with the conforming faces so close together that the curved surfaces provide a single airfoil, the curved surfaces being continuous except as the mounting means requires interruption.

Claim 16

In an aircraft having a body and with the capability of auto-gyrating, the combination of: a gimbal connector for the body, a rotor assembly distinct from the body and secured to the gimbal connector comprising a pair of structurally rigid circular rotors each bearing wind-driven blade elements projecting from its periphery, the rotors being profiled with conforming inner faces and curved outer surfaces, and means mounting said rotors for geared contrarotation on a common axis with the conforming faces spaces so close that the curved surfaces provide a single airfoil, and rotor-tilt means in said body.

Claim 17

In an aircraft having a body and with the capability of auto-gyrating, the combination of: a gimbal connector for the body, a rotor assembly distinct from the body and secured to the gimbal connector comprising a pair of structurally rigid circular rotors each bearing wind-driven blade elements projecting from its periphery, the rotors being profiled with conforming inner faces and curved outer surfaces, and means mounting said rotors for geared contrarotation on a common axis with the conforming faces spaces so close that the curved surfaces provide a single airfoil, and rotor-tilt means in said body.

Claim 18

The combination in accordance with claim 9 in which the spacing between the faces is in the inches order, down to less than one inch.

Claim 19

The combination in accordance with claim 9 in which the dihedral angles formed by geometrical intersections of the faces, if flat, and the blades remote and proximate to the body are, respectively, 5 and 5.5 degrees.

Claim 20

The combination in accordance with claim 9 in which the diameters of the rotors with their blades are on the order of nine feet.

Claim 21

The combination in accordance with claim 9 in which the angle of attack of the blades approximates two degrees.

Claim 22

An aircraft having a fusilage body and auto-gyrating, vertical lift and descent, forward flying and takeoff capabilities, comprising, in combination: a pair of rigid coaxial lift structures, one upper and one lower, each lift structure having a circular periphery and profiled to provide a curved surface and a face, said lift structures being positioned with their faces so close that the structures are effectively a single airfoil, individual sets of fixed blades uniformly distributed on and secured to the respective peripheries of said lift structures, lift structure mounting means having a single axis for mounting and gearing together said lift structures for counter-rotation on said axis, the curved surfaces and faces of said lift structures being continuous and uninterrupted except as required by the mounting means, gimbal means for securing the mounting means to said body, forward propulsion means in said body, means in said body for supplying variable power to said forward propulsion means on command of the pilot, means subject to command of the pilot for applying variable power from a source in the body to drive said lift structures, and means accessible from the body for controlling the tilt of the lift structures.

Claim 23

An aircraft having a fusilage body and auto-gyrating, vertical lift and descent, forward flying and takeoff capabilities, comprising, in combination: a pair of rigid coaxial lift structures, one upper and one lower, each lift structure having a circular periphery and profiled to provide a curved surface and a face, said lift structures being positioned with their faces so close that the structures are effectively a single airfoil, individual sets of fixed blades uniformly distributed on and secured to the respective peripheries of said lift structures, lift structure mounting means having a single axis for mounting and gearing together said lift structures for counter-rotation on said axis, the curved surfaces and faces of said lift structures being continuous and uninterrupted except as required by the mounting means, gimbal means for securing the mounting means to said body, forward propulsion means in said body, means in said body for supplying variable power to said forward propulsion means on command of the pilot, means subject to command of the pilot for applying variable power from a source in the body to drive said lift structures, and means accessible from the body for controlling the tilt of the lift structures.

Claim 24

An aircraft in accordance with claim 14 in which the means for applying variable power to drive the lift structures includes an overrunning clutch responsive to speed of the lift structures or command of the pilot.