Abstract: An airship with provisions for vectored thrust provided by a plurality of controllable pitch rotor thrust producing units attached to the elongated aerostat hull spaced from and on opposite sides of the center of overall mass of the airship. The pitch control systems for the rotors of all thrust units include collective and cyclic pitch controls of the main, horizontally rotating lifting rotors and the control systems are interconnected to be operable by a master control which establishes both similar and differential pitch settings of the rotors of selected thrust units in a manner to establish vectored thrust in directions which establish the required amounts of vertical lift, propulsion thrust, trim and control forces to control all flight aspects of the airship.

Abstract: A composite aircraft comprising a system of airfoils rotating about a horizontal axis providing lift and thrust in combination with a lighter-than-air gas containment bag providing bouyant lift; said aircraft being capable of lifting and transporting a load.

Abstract: An airship and a magnetically operated anchoring assembly adapted to provide rotation of the airship with respect to the ground, includes a gondola mounted to an envelope structure adapted to house lighter-than-air gas as well as any enclosures which may be used for containing the gas and a magnet device mounted to and operable from the gondola for attraction to a magnetically attractive anchoring structure secured to the ground. As preferably embodied, the magnet device is adapted to permit rotation of the gondola about the anchor point and the gondola is mounted to the envelope so as to be positionable at various desirable points under the longitudinal axis of the airship. Alternatively, the magnet may be mounted to a generally front-facing portion of the airship and the anchoring structure includes a mast with a magnetically attracting cylinder rotatably mounted to the mast at a height sufficient to enable mating with the magnet device on the airship.

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: 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: 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 balloon filled with buoyant gas provides the major part of the required lift. A pair of spaced rings are supported by a rigging having a plurality of lines supported by the upper half of the balloon at approximately the vertical center of the balloon. Each of a pair of helicopter blade units is rotatably mounted on a corresponding one of the rings. A frame is supported by the rigging beneath the balloon and has a passenger's bicycle type seat mounted thereon, a pedal-operated sprocket wheel rotatably mounted thereon and a plurality of landing wheels rotatably mounted thereon. The sprocket wheel is coupled to the helicopter blade units in a manner whereby a passenger seated in the seat and pedalling the sprocket wheel in any position between central and forward positions contrarotates the torque-balancing blade units for providing additional lift and forward propulsion force. A rudder is movably mounted on the frame and is controlled in direction by the passenger for directing the aircraft in flight.

Abstract: A winged aircraft, adapted to takeoff and land with its longitudinal axis at a very steep angle of inclination, including: balloons that have a center of buoyancy forward of the center of gravity and tend to turn the craft into the said steep angle; a controllable-thrust stern-elevating propeller in an upright wind tunnel, having a lift rearward of the center of gravity that in horizontal flight balances the torque of the balloons; and an elongated, stiffly resilient body frame of a multiplicity of inflated small tubes extending in the fore-and-aft direction, supported by longitudinally spaced, rounded ribs, disks or the like. This frame is round in the middle and somewhat streamlined at each end, its stern portion rearwardly sloping downward at its top and upward at its bottom. The assembly of tubes, preferably extending from the foremost to the rearmost parts of the frame, is flattened into substantially linear, horizontal shape at the rear portion.

Abstract: Various modifications are disclosed of the composite aircraft, which is the subject of U.S. Pat. No. 3,856,236 by this same inventor. The control console is supported from the center of the upper rotating balloon sphere instead of its south pole to reduce the periodic motion of the console about its point of attachment to the sphere. The console is supported from the center of an inner framework through a tapered indentation in the bottom of the sphere. A lift command control system determines the angle of attack of each wing about the periphery of the sphere to provide the force required to generate movement of the sphere in a preselected direction. If the wing experiences a gust, the force reaction compels the wing to seek a different angle of attack to keep the new force in balance with the command force exerted by the control on the wing to automatically provide gust control. A pneumatic lift command control system is illustrated.