Abstract: The invention provides for a cycloidal propeller, in strictly rudder operation, accessory apparatuses that mesh with a gear drive connected to a shaft of the respective wing. The invention accomplishes relatively small actuation movements of the accessory apparatuses, sufficient to achieve a large pivoting movement of the wings, so that the wings can be adjusted over large angles without impediment. Therefore, wings having normal profiles may be utilized.

Abstract: The present invention relates to an electric fan employing three impellers which are so implemented as to receive the driving force of the motor and, more particularly, to an electric fan equipped with the second crank device and the convex surfaced driving bevel friction wheel and driven bevel friction wheel to swing the fan impeller shaft up-down repeatedly and right or left simultaneously, and to an electric fan that has the carrying handle or the carrying handle with the wheels for the convenience of moving, and also to an electric fan that can separate the upper body from the lower body to establish itself as a short up-right standing type, an attache-to-ceiling type, or an attach-to-wall type, and to an electric fan that can get rid of blowing reaction by a stabilizer and, thus, stabilize the swing movement of the fan impeller.

Abstract: A swinging head gear shell for an electric fan is provided and includes a body and a cover respectively molded from reinforced engineering plastics. The body has a mounting plate for mounting with screws, a first open top chamber and a second open top chamber linked in parallel and adapted for receiving a swinging head gear. The body has a plurality of screw holes for the mounting of the cover, and a vertical locating barrel through which one gear shaft of the swinging head gear passes. The mounting plate has a circular through hole through which the worm of the swinging head gear passes. The cover overlays the body to close the first open top chamber and the second open top chamber, and has a plurality of mounting holes respectively fastened to the top screw holes of the body by screws. The cover has a raised portion, and a through hole formed in the raised portion in communication with the second open top chamber for the control lever of the swinging head gear to pass.

Abstract: An anti-drive device for restraining against rotation the stationary ring of a rotor control system of a rotary wing aircraft includes a drive tube driveably connected to an engine through a transmission, a rotating ring driveably connected to the drive tube and supported on the stationary ring, pitch links connecting the rotating ring to pitch arms of a rotor that supports rotor blades for rotation and for pivoting motion, and a four bar linkage connecting the stationary ring to the transmission casing. The linkage defines a nearly linear path along which its attachment to the stationary ring travels as the rotor and control system are axially displaced along the rotor shaft and angularly tilted in accordance with the selective actuation of control servos attached to the stationary ring.

Abstract: The invention relates to a control device for monocyclic pitch in a fixed reference system and multicyclic pitch in a rotating reference system, for the blades (7) of a rotor craft.In addition to conventional swashplates (27, 38), one (38) of which rotates (39) on the other (27) held in rotation by a nonrotating compass (28), but which slides axially (4) and oscillates (25) about the rotor mast (1), through the action of pilot control (30), it comprises multicyclic jacks (45) in a number equal to the blades (7), and each of which is implanted in the rotating plate (38) and directly drives a pitch control rod (44) of a corresponding blade (7). Each multicyclic jack (45) is a dual-action, hydraulic linear jack controlled by a servovalve (49) also implanted on the rotating plate (38).

Abstract: The adjustable propeller has an adjusting mechanism for adjusting the pitch of the individual propeller blades. The adjusting mechanism comprises an actuator and a correction mechanism for each propeller blade for cyclically adjusting the pitch angle of a related propeller blade under the control of a control device.

Abstract: A rotor control system for a helicopter in which the conventional swashplate is eliminated and the rotor hub is integrated to include an actuator for each rotor blade. Two arrangements are employed, each of which utilizes a hydraulic circuit. One arrangement is a hydromechanical arrangement with stick control, while the other arrangement is an electro-hydraulic fly by wire arrangement. The latter does not employ a swashplate, while the former employs a modified swashplate. The controls, like the actuators, are mounted in the rotor hub, and the hydraulic lines and fiber optics pass through the rotor drive shaft to the rotor hub.

Abstract: In a helicopter having a power shaft with a main axis and bearings for supporting an even number of blades for pivoting about their longitudinal axes, arms mounted on the respective blades for pivoting them in the same and opposite directions for cyclic and total pitch control, respectively, a featured control lever mounted intermediate its ends on a first pivot which lies in a first plane in which the main axis lies, with the control lever having movability of first and second kinds bodily with its pivot axis in the first plane and rockable about its pivot axis, respectively, links connecting the ends of the control lever with the free ends of the arms for pivoting the blades in first and second directions on movements of the control lever of the first and second kinds, respectively, an axially immovable control shaft turning with the power shaft, a swashplate mounted on the control shaft for universal movement on the latter, a first operating connection between the swashplate and first pivot, and including

Abstract: A helicopter rotor having blade trailing edge tabs which are actuated in response to control rod loading to reduce or cancel the blade pitching moments imposed upon the blade and hence the control rods by blade aerodynamic and inertial loads, or other loads, encountered during rotor operation.

Abstract: Individual blade control of a helicopter rotor is accomplished by rotation of a mast (10) about a standpipe (12) where an individual blade (16) is coupled to the mast through a hub (18). Pilot input signals are transmitted by fly-by-optic transmission lines (14) through a fiber optic slip ring (40,42) to signal generators (134, 136, 138) for each of three sections of triplex actuators (76-79) coupled to individual rotor blades. Hydraulic fluid for positioning each of the actuators (76-79) is provided by electrohydraulic power packages (88, 90 and 92) where each package includes a pump and alternator. As each blade rotates about the mast (76) the pitch angle changes by individualizing the output of the signal generators (134-138) for each actuator.

Abstract: Cyclic pitch variation of the rotor blades of a horizontal axis wind energy conversion machine permit its operation at substantially design rotor speed and rotor torque over a range of wind speeds, by heading the rotor progressively out of the wind through a range from approximately 20.degree. for light winds to a near 90.degree. setting for gales, at which the power output is interrupted to permit the rotor to idle. Changes in wind direction will cause the rotor to follow the wind even though so headed out of it. By allowing the blades substantial freedom to adapt their pitch to side winds, the present construction allows rapid rates of yaw into a shifting wind, such as may destroy conventional rotors by the attendant gyroscopic forces. Further, by actively controlling their pitch, aerodynamic forces exerted by the cyclic pitch change blades substantially balance out the gyroscopic forces attendant to yaw.