Sikorsky Aircraft Corporation

Other

United Technologies Corporation

Rogue Wave Industries, LLC

Corey D Jones

David A Kovalsky

Kevin P Leahy

William C Reinfelder

Grant A MacLennan

Hans Wennerstrom

Frank M Caputo

Leon M Meyer

Jeffry C Purse

Kevin P Viola

Steve Sucic

Christopher J Damon

Marshall T Long

William Degnan

The invention comprises an inductor, such as used in processing transmission of a 3-phase power system. The inductor comprises a flat/rectangular winding with a narrow edge of the flat winding wound around a core, where the width of the winding exceeds three times the height of the inductor facing edge of the winding. The inductor optionally comprises a distributed gap particle core and/or is wound in parallel with multiple windings. Optionally, the inductor is used as part of an equal coupling common mode electrical system for processing the 3-phase transmission and/or a high frequency inverter comprising a switching device, such as a silicon carbide metal-oxide-semiconductor field-effect transistor.

Flat winding / equal coupling common mode inductor apparatus and method of use thereof

A method of constructing a mandrel generally complementary to a spar cavity of a spar includes connecting a first component and a second component to form a central space there between and inserting a center component within the central space such that the center component retains the first component and second component in a desired position forming an outer surface of the mandrel which corresponds to an inner surface of the spar cavity.

Method of assembling a composite spar removable mandrel

The invention comprises an electrical system apparatus for processing three-phase power, comprising: a first, second, and third inductor connected on a first end to a first common magnetic field carrying plate and connected on a second end to a second common magnetic field carrying plate, where the three inductors are equidistant from each other and/or equidistance from a central axis, which yields an equal coupling common mode inductor-capacitor based filtering apparatus. Generally, inductor placement symmetry and/or equal magnetic field permeabilities between each pair of the three inductors balances magnetic fields within each inductor at each point of time, where each of the three inductors is connected to a single phase of three-phase power, the three phases offset from each other by one-third of a period.

Equal coupling common mode inductor apparatus and method of use thereof

A syringe measurement marking system for use with a syringe that includes a barrel and a plunger is marked with patient-based numerical measuring indicia on the plunger. The patient-based numerical measuring indicia is non-volumetric in nature and instead indicates patient dosing criteria such as weight, age, height, blood sugar level, or any other patient criteria by which dosing is determined. The plunger may contain more than one set of patient-based numerical measuring indicia, such as one set for adults or one set for pediatrics, or one set for a first dose of a medication and one set for a second dose, or one set based on weight in pounds and one set based on weight in kilograms. The syringe barrel will contain one or more measurement lines.

Syringe measurement marking and dosing system

A weight training device comprising a hollow tubular body. A plurality of handle wells disposed in the hollow tubular body. A plurality of handles disposed in the handle wells, wherein the plurality of handles comprise axially-oriented handles and circumferentially-oriented handles, and wherein the axially-oriented handles are diametrically opposed to the circumferentially-oriented handles. A fill cap well disposed in the hollow tubular body. A fill cap disposed in the fill cap well and removably attached to the hollow tubular body, wherein the fill cap is threaded and is attached to a threaded extrusion of the hollow tubular body. A plurality of baffles disposed within the hollow tubular body, wherein the hollow tubular body is configured to be used partially filled with a fill material so as to create a randomly variable weight distribution. Two diametrically-opposed end caps are attached to the axial ends of the hollow tubular body.

Weight training device and method of use

A main rotor blade includes a tip section having a splice cap, a structural tip spar, a core and an upper and lower tip skin. The tip section is mounted to a central blade section by mounting the tip spar to a main blade spar. The tip spar includes a first surface substantially parallel to a second surface. The first and second surfaces each extend from a shear web therebetween to define the generally C-shape in cross section. The shear web generally carries rotor blade torsional loads and eliminates the heretofore required structural core. A section of the tip spar overlaps a section of the main blade spar. The tip section thereby transfers the loads carried thereby through interaction between the overlapped spar sections. The tip section core and skins need not be structural members as the tip spar carries rotor blade tip section torsional loads.

Rotor blade tip section

A composite tip cap assembly for a helicopter main rotor blade includes a composite main fairing, a unitary composite rib detail internally integrated in combination with the composite main fairing, a composite closure fairing bonded in combination with the composite main fairing, and an abrasion strip bonded in combination with the composite main fairing and the composite closure fairing.

Composite tip cap assembly for a helicopter main rotor blade

An apparatus for installing a leading-edge sheath onto a helicopter main rotor blade subassembly, including a lower assembly having a leading-edge sheath contour nest configured for supporting the leading-edge sheath, opposed carriage members connected to a base, wherein each of the opposed carriage members supports a plurality of suction cups and is capable of synchronized translational movement relative to the leading-edge sheath contour nest between an engaged position wherein the plurality of suction cups are in abutting engagement with the leading-edge sheath, and a disengaged position where the plurality of suction cups are disengaged from the leading-edge sheath. A vacuum system is connected in fluid communication with the plurality of suction cups and is capable of providing vacuum pressure to the plurality of suction cups, whereby the vacuum pressure generates suction forces between the plurality of suction cups and the leading-edge sheath when the opposed carriage members are in the engaged position. An upper assembly is disposed in combination with the lower assembly, and comprises a plurality of stanchions connected to the base of the lower assembly, and a contour clamp connected to each of the stanchions capable of translational movement relative to the leading-edge sheath contour nest. The contour clamps are configured for supporting the helicopter main rotor blade subassembly and function to facilitate insertion of the helicopter main rotor blade subassembly into the leading-edge sheath.

Apparatus for installing a leading-edge sheath onto a helicopter main

An apparatus for assembling a helicopter main rotor blade subassembly which includes a lower airfoil skin, a core, an upper airfoil skin, and a spar assembly having a tip end and a root end, the apparatus including a lower assembly including a base having a contoured upper airfoil nest, wherein the contoured upper airfoil nest has a root end and a tip end, at least two guide ramps disposed proximal to the contoured upper airfoil nest, wherein at least one of the guide ramps is disposed proximal to the root end and at least one of the guide ramps is disposed proximal to the tip end, and a plurality of leading-edge pusher cams disposed proximal to the contoured upper airfoil nest. An upper assembly configured for mating with the lower assembly is provided, and includes a support structure and a flexible impervious membrane supported by the support structure, wherein the flexible impervious membrane and the contoured upper airfoil nest define a molding cavity therebetween upon mating of the upper assembly to the lower assembly.

Apparatus for assembling a helicopter main rotor blade subassembly

A method for fabricating a helicopter blade subassembly includes the steps of providing a blade compaction apparatus having a lower assembly configured for mating with an upper assembly. The lower assembly includes a base having a contoured upper airfoil nest with at least two guide ramps and a plurality of leading-edge pusher cams disposed proximal thereto. The upper assembly includes a support structure supporting a flexible impervious membrane, wherein the flexible impervious membrane and the contoured upper airfoil nest define a molding cavity therebetween upon mating of the upper assembly to the lower assembly. The method further includes disposing the upper airfoil skin and the core in combination with the contoured upper airfoil nest, and then connecting a tip end support insert and a root end support insert in combination with the spar assembly, wherein each of the support inserts include guide members. The spar assembly is located in chordwise alignment in the contoured upper airfoil nest by driving the guide members into conics in the guide ramps and driving the spar assembly into a core conic with the leading-edge pusher cams. The lower airfoil skin is then disposed in combination with the core and the spar to form the helicopter blade subassembly, and then the upper assembly is mated to the lower assembly. The air within the molding cavity is then evacuated such that evacuating the air causes the flexible impervious membrane to apply compaction forces to the helicopter blade subassembly.

Methods for fabricating a helicopter main rotor blade

Fiber reinforced composite spar for a rotary wing aircraft and method of

A fiberglass or other material skin is applied to a composite airfoil structure in a mold assembly having a partially compliant caul plate component which defines the shape of the lower surface of the airfoil. The caul plate component includes a first portion which is essentially rigid and which covers the leading edge of the airfoil. The rigid portion of the caul plate component provides improved conformation of the airfoil skin to the leading edge of the airfoil. The caul plate component also includes a compliant portion which covers and defines the shape of the trailing edge of the lower surface of the airfoil. The stiffness of the caul plate component also has a variable stiffness zone which interconnects the rigid and compliant portions thereof. The use of rigid and compliant portions on the caul plate provides for a controlled conformance of the skin to the leading edge of the airfoil, while allowing the skin to accurately conform to the remainder of the airfoil in spite of variations in the dimensions of internal operating components of the airfoil.

Method for applying a skin layer to an airfoil structure

The described embodiment of an edge-of-part (EOP) scribe device is operative to simultaneously scribe opposed trim lines in an oversized, cured leading-edge sheath mounted on a sheath mold assembly. The EOP scribe device includes a primary carriage assembly having rollers secured thereto wherein the primary carriage assembly is translatable along side rails secured to the sheath mold assembly, opposed pairs of guide rails affixed to the primary carriage assembly, and a secondary carriage assembly mounted in movable combination with each pair of guide rails. Each secondary carriage assembly includes a spring-loaded scribe head for inscribing a trim line in the cured leading-edge sheath, a rigid follower linkage secured to the secondary carriage assembly, and a follower slide roller mounted in rotatable combination with the rigid follower linkage and operative to rotatably engage a trim line template mounted on the sheath mold assembly. As the primary carriage assembly is subjected to translation along the sheath mold assembly, dimensional changes in the trim line templates induce vertical displacements in the follower slide rollers, the induced vertical displacements being coupled through the rigid follower linkages to cause corresponding vertical displacements in the secondary carriage assemblies and concomitantly, in the scribe heads. The vertical displacements of the hardened scribe heads matches the respective trim line templates such that the scribed trim lines correspond to the profiles of the finished edges of the prefabricated leading-edge sheath.

EOP scribe device

Apparatus and methods for fabricating a helicopter main rotor blade include a compaction fixture for assembling and compacting blade subassembly components and a sheath spreading/insertion apparatus for spreading and inserting a leading-edge sheath onto the blade subassembly during the compaction process. The compaction fixture includes a lower assembly having a contoured upper airfoil nest mounted in combination with a support structure and an upper assembly having a pressure bag affixed in sealed combination to a contoured backplate affixed in combination to a structural support truss. The contoured upper airfoil nest includes a plurality of tooling pins for locating an upper composite skin in aligned combination on the contoured upper airfoil nest and a plurality of pusher pins for chordwise alignment of a spar assembly in the contoured upper airfoil nest. Spar stanchions affixed to the support structure provide spanwise alignment of the spar assembly in the contoured upper airfoil nest. With the upper and lower assemblies in locked combination, the pressure bag is pressurized to compact the assembled blade subassembly components. The sheath spreading/insertion apparatus includes a movable stanchion, upper and lower elongate carriage members mounted in synchronized movable combination with the stanchion, and a row of suction cups mounted in combination with each carriage member. Pneumatic cylinders are mounted in combination with the stanchion and the respective carriage members.

Growing community of inventors

Prospect, CT, United States of America

Corey D Jones