Sikorsky Aircraft Corporation

Leon M Meyer

David N Schmaling

Richard C Lay

Corey D Jones

Timothy James Conti

David A Kovalsky

Andrew Paul Scott

Christopher J Damon

Fran Byrnes

Anthony Stephen Drago

Yih-Fam Chen

Edwin Mark Hafner

Brian Rothermich

Yih-Farn Chen

A flexbeam rotor blade assembly includes a flexbeam having a body that includes a first surface, a second, opposing surface, and an opening extending through the first and second surfaces. At least one snubber is mounted to one of the first and second surfaces spaced along the body from the opening. A snubber retainer is mounted to one of the first and second surfaces between the body and the at least one snubber. The snubber retainer includes a retainer plate having a snubber attachment member to which the snubber assembly is mounted and a mounting arm including a retainer plate opening spaced from the snubber attachment member. The retainer plate opening registers with the opening in the flexbeam. A mechanical fastener extends through the retainer plate opening and the opening in the flexbeam. The mechanical fastener joins the snubber retainer to the one of the first and second surfaces.

Rotor blade snubber retainer for a rotary wing aircraft

A trim tab for use in a blade housing includes a cavity connected to an opening extending from the cavity out a trailing edge of the blade housing, the cavity has a first dimension which is greater than a second dimension of the opening at a same spanwise location of the blade housing. The trim tab has a trim portion, a head portion having a head dimension substantially similar to the first dimension, and a tail portion connecting the trim portion and the head portion. The tail portion has a tail dimension substantially similar to the second dimension such that the trim tab is retainable by the blade housing when the head portion is disposed within the cavity and the tail portion is disposed within the opening.

Trim tab retention system, an aircraft employing same and a method of retaining a trim tab within a blade housing

A control horn arrangement includes a control horn body with an inboard end and an opposed outboard end. The control horn body defines a torque tube axis which extends between the inboard and outboard end of the control horn body. An inner flange and an outer flange are disposed on the outboard end of the control horn body. The inner flange and the outer flange extend about the torque tube axis and define between one another a receptacle to fix a torque tube to the outboard end of the control horn body.

Rotor blade control horn arrangements

A system and method to substantiate safe-life criteria of a structure with an anomaly includes a flaw in a critical loaded region of a test structure; a processor; and memory having instructions stored thereon that, when executed by the processor, cause the system to receive first signals indicative of strain energy release rates (SERR) for the flaw at the critical loaded region of a test structure; fit the first signals for the flaw SERR to a Benzeggah-Kenane (B-K) mixed mode curve shape; determine values indicative of B-K criteria of the test structure in response to the fitting of the first signals; receive second signals indicative of SERR for the production structure; and compare the second signals with the B-K criteria of the test structure to substantiate the safe-life criteria.

Fracture mechanics based method for composite damage tolerance criteria

A method of assembling a rotor blade includes determining first spanwise and chordwise moments of a first component of the blade and comparing the first spanwise and chordwise moments to respective target first spanwise and chordwise moments. The first spanwise and/or chordwise moment(s) of the first component is/are adjusted based upon corresponding results of the comparison to provide balancing of the first component. Second spanwise and chordwise moments of a second component of the blade are determined and compared to respective target second spanwise and chordwise moments. The second spanwise and/or chordwise moment(s) of the second component is/are adjusted based upon corresponding results of the comparison to provide balancing of the second component. The balanced first and second components are assembled to each other so that target spanwise and chordwise moments of the blade are met.

Method for static balancing of aircraft rotor blades

The invention relates to a backing plate used for an elastomeric bearing system, the backing plate comprising a plate which defines an at least partial annulus about an axis, a motion limiter and a redundant pivot which extend from the plate so as to respond to a retainer plate disbond.

Elastomeric bearing system motion limiter

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.

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Harwinton, CT, United States of America

Leon M Meyer