United Technologies Corporation

Sikorsky Aircraft Corporation

Kevin A White

Stephen V Poulin

David H Hunter

Frank Paul D'Anna

Leonard J Doolin

Steven M Capelle

Robert James Milne

Kenneth L Lauck

Robert J Milne

Dave H Hunter

Robert F Bohm

Kwok Chin

John H Engelmann, Jr

Robert J Trembicki

A rotor hub configured to support and rotate a plurality of rotor blades about an axis of rotation is includes a cylindrical body having a central shaft hole including the axis of rotation. The shaft hole has a radius extending from the axis of rotation radially. A plurality of radial spokes extends from the cylindrical body in a spoke direction. A plurality of arcuate segments extends between the distal ends of adjacent spokes to define a plurality of hub apertures. The spoke direction extends at an angle to the radial direction in both the horizontal plane, and a vertical plane, perpendicular to the horizontal plane. A line defined by the spoke direction does not intersect the axis of rotation. The spoke direction extends at an angle in the horizontal plane in a direction opposite to a direction of rotation of the rotor hub about the axis of rotation.

Rotor hub for rotary wing aircraft

A mounting arrangement (60) for coupling a control rod (38) to a stationary swashplate member (32) of a helicopter swashplate assembly (30) wherein the mounting arrangement (60) is characterized by a specially configured stationary swashplate member (32) and a trunnion fitting (62) for mounting in combination therewith. More specifically, the stationary swashplate member (32) includes a horizontal web (74) disposed between an inner ring segment (72.sub.IR) and an outer ring segment (72.sub.OR), wherein the horizontal web (74) includes an aperture (78) and defines a mounting surface (74.sub.S). The trunnion fitting (62) includes a base (64) defining a mounting surface (64.sub.S) and a pair of mounting ears (66) having aligned apertures (66.sub.O). The mounting surface (64.sub.S) of the trunnion fitting (62) engages the mounting surface (74.sub.S) of the horizontal web (74) such that the mounting ears (66) are disposed through the aperture (78) of the horizontal web (74). The mounting arrangement (60) further includes a mounting device (80) for demountably affixing the trunnion fitting (62) in combination with the horizontal web (74) and a coupling device (84), disposed in combination with the aligned apertures (66.sub.O), for coupling the control rod (38) in combination with the trunnion fitting (62).

Control rod mounting arrangement for helicopter swashplates

A pitch actuation system restraint (PASR) device that provides, inter alia, protection for the pitch actuation system of a helicopter having a main rotor assembly configured for main rotor blade folding operations. The PASR device includes permanent adapter brackets that are permanently mounted in combination with the rotor hub arms of the main rotor assembly. The PASR device further includes a temporary adapter bracket and quick release pins for each main rotor blade to be folded. Prior to implementing blade folding operations, a temporary adapter bracket is temporarily secured in combination with the pitch control horn of each main rotor blade to be folded and the permanent adapter bracket of the adjacent rotor hub arm by means of the quick release pins. Each temporary adapter bracket and permanent adapter bracket as temporarily secured in combination functions as a rigid structural interconnection between the corresponding pitch control horn and the main rotor hub assembly that effectively locks the pitch control horn in position during blade folding operations such that displacements induced in the main rotor blade during blade folding operations cannot be coupled into the pitch actuation system.

Pitch actuation system restraint device for a helicopter blade folding

A blade retention pin system is operative to secure the blade cuff of a main rotor blade of a helicopter in combination with a spindle assembly of the main rotor hub assembly for main rotor assembly operations and is readily reconfigurable to accommodate blade folding operations. The blade retention pin system includes first and second pin assemblies, each pin assembly including a retainer pin and a handle subassembly, which includes a retainer member and a spring member in superposed abutting combination, pivotably mounted in combination therewith. The first pin assembly includes, in addition, a safety pin subassembly secured in combination therewith. Each retainer pin is inserted into aligned apertures of the blade cuff and spindle assembly and locked in place by pivoting the handle subassembly from an unlocked to a locked position wherein the retainer member engages the retainer pin and the spring member is biased onto the retainer pin to abuttingly engage the retainer member.

Blade retention pin system for a helicopter blade folding system

An improved flexible boot 20 is provided for protecting aircraft operating mechanisms such as bearing 18 from foreign objects such as sand and dirt. The boot 20 has a slit 30 and an associated resealing arrangement 39 which allows the slit 30 to be resealably closed. The resealing arrangement 39 thus enables the protected mechanism or bearing 18 to be inspected without removal of, or damage to, the boot 20 while still allowing the boot to retain its ability to protect the bearing 18 from foreign object damage. The preferred resealing arrangement 39 is of the hook and loop type which is sold under the registered trademark Velcro.RTM..

Resealable protective boot

A flexible composite scissor assembly is disclosed which utilizes one or more composite straps disposed either in a radial or non-radial relationship between a hub attached to a rotor and an inner or outer ring of a helicopter swashplate. The composite material has sufficient edge-wise stiffness to allow effective torque transmission between the rotor shaft and the swashplate yet has sufficient flexibility to allow for a vertical and angular displacement of the swashplate relative to the rotor shaft. Utilizing a flexible composite scissor assembly eliminates the need for mechanical linkages having pins and bearings which are a frequent source for wear, increasing the reliability of the rotor assembly, while reducing weight.

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Shelton, CT, United States of America

Kevin A White