Abstract: Feathering propeller particularly for auxiliary engines of sailing boats. The propeller comprises a device for transmitting a rotary and a positioning motion to the blades including planetary gear means for converting an angular motion of the drive shaft into an angular motion for inclining the propeller blades and means for halting the angular motion to halt the blades at the required inclination and render the blades of such inclination rigid both with the relative hub and with the drive shaft.

Abstract: A deployable stowed rotor having a rotor hub to which a pair of telescoping otor blades are connected is foldable into a package suitable for stowage prior to use. When the rotor is deployed, for example, as a lifting device for an ejection seat, positive preconing of the blades is provided by a spreading link arrangement connected to a drogue chute. Further coning during rotor spin-up is synchronized by intermeshed gears provided at respective one ends of the blades attached to the hub by teeter link hinges. Rotor speed is automatically regulated by a governing spring formed in conjunction with a helical spline arrangement between each of the blades and the hub and which varies the pitch of the spinning blades according to rotational velocity.

Abstract: A universally flexible rotor mast for a rotary wing aircraft wherein the universal flexing of the mast is accomplished by the use of multiple elastomer mounts of elastomer metal plate sandwich formation and with high strength cables embedded in the elastomer and anchored to opposing metal plates of the sandwich mounts. A static on-ground rotor mast lock is employed to secure the rotor mast in an upright position, the mast lock is used in conjunction with the elastomer mounts of the flexible mast.

Abstract: A deployable stowed rotor having a rotor hub to which a pair of telescoping otor blades are connected is foldable into a package suitable for stowage prior to use. When the rotor is deployed, for example, as a lifting device for an ejection seat, positive preconing of the blades is provided by a spreading link arrangement connected to a drogue chute. Further coning during rotor spin-up is synchronized by intermeshed gears provided at respective one ends of the blades attached to the hub by teeter link hinges. Rotor speed is automatically regulated by a governing spring formed in conjunction with a helical spline arrangement between each of the blades and the hub and which varies the pitch of the spinning blades according to rotational velocity.

Abstract: A vertical take-off and landing aircraft features an improved tail-lifting rotor and rotor directional controls. A new type of suction pressure jet-mechanical-flap rotor blade with a higher coefficient of lift is employed. The aircraft has a mechanism for loading and unloading passengers and a more efficient method of handling baggage and cargo. A much more efficient utilization of space in the fuselage is achieved through a reduced height passenger space and overhead rotor storage compartment.

Abstract: A fluid pump including a shaft arranged to be rotatably driven by a motor of the like which includes one or more blades pivotally mounted at their inner ends on the shaft so as to be freely pivotal during the rotation of the shaft into an equilibrium angular position throughout an angular range extending in both directions from a 90.degree. position and in an axial plane with respect to the axis of the shaft.

Abstract: A propeller such as a ship's propeller or screw comprises at least one propeller blade, and a propeller drive shaft. The propeller blade is mounted on the propeller drive shaft by employing a hub having a free end secured on the propeller drive shaft. The hub is provided with a central bore in the free end thereof. A pivot axis is defined mounted within the hub and perpendicular to the axis of the drive shaft. The pivot axis comprises a pivot shaft.The blade is pivotally mounted about the inner end of the blade freely about the pivot shaft, the pivot shaft intersecting the longitudinal direction of the blade. Abutment means for the blade are provided for limiting the free pivotal movement of the blade between two extreme positions at either side of the position in which the propeller blade extends substantially perpendicular to the axis of the shaft. The abutment means comprises a pair of abutment members secured in the bore to serve as abutments for the blades.

Abstract: The present invention relates to a propeller with retractable blades arranged on a hub, said hub being limitedly rotatable in relation to the propeller drive shaft, each of said blades being pivotable between an outward working position and an inward inactive position, whereby power and movement transmission means determining the pivoting position of the blades unites the drive shaft and the blades and is arranged at least when the propeller rotates in one of its both directions of rotation to compulsorily open out the blades by mutual turning movement between the drive shaft and hub. The propeller is particularly, but not exclusively, intended for competition sailing boats to give the least amount of resistance when the boat is under sail and the propeller retracted. Previous constructions have not functioned completely reliably in practice, especially not when reversing.

Abstract: A stirring device employs a shaft-mounted hub with five axially nested, radially extendable fins shaped to not only provide compact nesting of five fins to enter a bung opening of a drum, but also to provide ample surface area when extended for stirring.

Abstract: A basic lightweight helicopter frame is strapped to the body of a pilot and includes vertical side bars interconnected above the pilot's head to rotatably support a bladed rotor assembly and carry a rearwardly extending tail rotor assembly. The lower ends of the side bars carry fuel tanks from which rocket engines at the tips of the rotor blades draw fuel. A control assembly is supported at the upper end of the frame and extends forwardly therefrom for easy access by the pilot. The aircraft includes an attachable landing gear and an attachable pusher blade and engine assembly which can be used when desired.

Abstract: A hollow mixing bar having at least one blade pivoted at one end by attachment to the mixing bar such that it is designed to rest against the mixing bar until the mixing bar is rotated. As the mixing bar is rotated the unattached end of each blade moves away from the plane of the mixing bar thereby contributing to the blending or decompaction action of the mixing bar. The blade can also protect apertures in the mixing bar used for introduction of fluid materials through the mixing bar and the outlet apertures. The design of the mixing bar is especially advantageous in that it minimizes the initial torque necessary to blend or decompact solids and is readily removable for cleaning. In the preferred embodiment the mixing bar provides a wide range of blending action ranging from gentle vibration to violent agitation.

Abstract: An omnidirectional turbine providing a rotational output of one sense in response to fluid flow approaching the turbine from any direction parallel to its plane of rotation. The invention is contemplated for use in conjunction with electric generators or power generating systems in general capable of utilizing power output from said turbine.

Abstract: Device for diminishing tip vortices in an aircraft. For the purpose of diminishing the tip vortices generated by aircraft there are provided retractable foils at or near the airfoil, as wing, tips in question and projecting upwardly and/or downwardly therefrom. The operation of the retractable foils is satisfactory if such foils are parallel to the centerline of the aircraft but it is preferable if such foils are angled slightly with respect thereto, such as if the leading edge of the upper foil is angled approximately 10.degree. inwardly toward the fuselage of the aircraft and the bottom foil is oppositely angled also approximately 10.degree.. The retractable foils, in addition to diminishing wing tip vortices, also when used on wing tips improve the rate of climb of an aircraft at a given engine setting and appear to diminish the area over which the major amounts of noise generated by the aircraft will be dispersed.

Abstract: A deployable stowed rotor having a rotor hub to which a pair of telescoping otor blades are connected is foldable into a package suitable for stowage prior to use. When the rotor is deployed, for example, as a lifting device for an ejection seat, positive preconing of the blades is provided by a spreading link arrangement connected to a drogue chute. Further coning during rotor spin-up is synchronized by intermeshed gears provided at respective one ends of the blades attached to the hub by teeter link hinges. Rotor speed is automatically regulated by a governing spring formed in conjunction with a helical spline arrangement between each of the blades and the hub and which varies the pitch of the spinning blades according to rotational velocity.

Abstract: A folding boat propeller assembly having a hub and two blades. The radially inner portion of each blade is pivoted to the hub. Upon forward movement of the boat, the blades will automatically be pivoted rearwardly into a closed folded-together position by water resistance. Upon rotation of the hub by the boat's engine, the blades pivot outwardly and forwardly to a driving position.

Abstract: There is disclosed a propeller adapted for driving a vehicle, such as a boat. The propeller comprises a pair of pivotally mounted propeller blades which are adapted to assume an inactive position wherein the blades are substantially aligned with the direction of vehicle movement, and a working position wherein the blades are at an angle with respect to the direction of vehicle movement. A stop means on the propeller limits the forward pivotal movement of the propeller blades to those locations between the inactive position and a stop position wherein the propeller blades each forms an oblique angle with respect to the inactive position so the propeller blades can each assume a working position which is located on either side of a perpendicular position wherein the propeller blades are perpendicularly disposed to the direction of vehicle movement.

Abstract: A helicopter main rotor which can be supported in two positions of elevation above the fuselage, and apparatus and method for moving the helicopter rotor with blades attached from a first elevated position above the fuselage wherein the rotor is supported from an extension shaft projecting from a first shaft to a second elevated position above the fuselage wherein the rotor is supported from the first shaft.

Abstract: A convertible auxiliary turbine capable of providing turbopropeller thrust interchangeably with pure jet propulsion, comprising a controllable fluid deflector element, and an inverted free-floating rotor having planular drive-vanes aligned with the normal flow direction of the engine's gas stream. Thus, no rotative force is imparted to the turbine until the flow direction is varied. At a given change, the turbine begins to spin, outboard swingable propeller blades are urged to open by action of centrifugal force, and propeller thrust is generated in ratio to the angle of deflection, with jet power in inverse ratio thereto.