Sikorsky Aircraft Corporation

Scott A Chasen

William Arthur Welsh

Chris John Biehl

Jon McBride

Joseph Lawrence Simonetti

Donald William Lamb, Jr

Barton J Hainsworth

Richard S Barnard

Anthony Zbigniew Stobiecki

Stephen Johnston

Robert R Rogstad

Steven Bofill

Michael H Ambrose

Joseph Caterisano

Robert W Maxwell

A method for securing an engine using an adjustable mounting assembly is provided including adjusting an extendible element of the adjustable mounted assembly from a first position to a second position. Another extendible element of the adjustable mounting assembly is adjusted from a third position to a fourth position. The engine is mounted using the adjustable mounted assembly with the extendible element in the second position and another extendible element in the fourth position.

Articulated mounts

An active vibration control system for an aircraft includes a gearbox operably coupling a power source and a component rotatable about an axis. The gearbox includes a flexible region which allows flexure between a first stage and a second stage. At least one active vibration control actuator is arranged in vibrational communication with the flexible region to counteract vibrations transmitted between the power source and the rotatable component.

Case mounted transmission AVC force generators

A flexible fuel bladder assembly for an aircraft includes a flexible fuel bladder positioned at an airframe and having an opening to allow a flow of fuel into and/or out of the fuel bladder. A breakaway valve is operably connected to the fuel bladder at the opening to control a flow of fuel therethrough. A non-contacting or loose fitting reaction feature is affixed to the airframe and is interactive with the breakaway valve such that movement of the breakaway valve relative to the reaction feature results in breakage of a valve body of the breakaway valve and closure of the breakaway valve to prevent flow of fuel therethrough while also allowing for a second reaction mode to cause breakage of a valve body should the connecting hose be pulled relative to the breakaway valve.

Fuel system breakaway valve reaction bridge and reaction collar

A strut for mounting an engine in an aircraft includes a first member and a second member. A friction material is coupled to a surface of the first member and is positioned between the first member and the second member. At least one attachment couples the first member, the second member, and the friction material. A biasing mechanism is associated with the at least one attachment. A biasing force of the biasing mechanism biases the second member into engagement with the frictional material to create a static frictional load between the first member and the second member.

Dual mode supplemental strut and damper

A method of securing two components to each other includes locating a mounting strip at a first mounting flange of a first component. The mounting strip is slidably affixed to the first component and includes a plurality of strip openings and a tightening ramp located at each strip opening of the plurality of strip openings. A second component is located such that a second mounting flange of the second component abuts the first mounting flange. A plurality of fasteners are located at the second mounting flange. A fastener of the plurality of fasteners extends through each strip opening of the plurality of strip openings. The mounting strip is slid in a direction to increase tension on the plurality of fasteners via an increasing height of the tightening ramp under a fastener head of the fastener, thereby securing the first mounting flange to the second mounting flange.

Engine inlet duct installation

An engine inlet assembly includes an inlet duct having a first inlet duct leg and a second inlet duct leg, the first inlet duct leg and the second inlet duct leg extending toward a common inlet duct outlet located at an engine inlet. The first inlet duct leg and the second inlet duct leg are fixedly secured to an airframe of an aircraft at an air inlet. The duct outlet has a floating interface with the engine inlet.

Engine inlet configuration

An eccentric fitting assembly includes an outer eccentric fitting which defines an outer axis, the outer eccentric fitting defines an opening offset from the outer axis and an inner eccentric fitting which defines an inner axis, the inner eccentric fitting defines a stud opening offset from the inner axis, the inner eccentric fitting receivable within the opening.

Eccentric fitting assembly

A telescoping aerial refueling probe includes a second section and a ball screw. The first section is telescopically mounted to the second section. The ball screw is rotationally mounted along the longitudinal axis of the probe. A hydraulic motor rotates the ball screw to drive a ball screw nut and attached first section relative the second section. The hydraulic motor communicates with the hydraulic system and is operated in response to a control system. A backup motor such as an electric motor alternatively drives the ball screw upon failure of the hydraulic motor. As only the backup motor is required for redundancy, minimal additional weight is added to the probe and a relatively compact system is provided.

Telescoping refueling probe

A fuel intake device (20) for a fuel system (10) having a fuel tank (14) for containing a supply of fuel (16) and an internal fuel feed line (18) which is disposed internally of the fuel tank (14) and which extends into a sump region (26) thereof. The fuel intake device (20) is characterized by a filter assembly (40) which envelopes an end portion (18.sub.E) of the internal fuel feed line (18) and which includes a lower fuel filtering portion (42) and an upper fuel bypass portion (44). The lower fuel filtering portion (42) has a plurality of fine apertures (42.sub.O) therein for facilitating a primary flow (P.sub.F) of fuel (16) therethrough and for filtering debris from the supply of fuel (16) in a normal operating mode. The upper fuel bypass portion (44) has a plurality of coarse apertures (44.sub.O) for facilitating a secondary flow (S.sub.F) of fuel therethrough in a bypass operating mode. Furthermore, the filter assembly (40) is situated about the end portion (18.sub.E) such that the inlet orifice (18.sub.O) thereof is disposed internally of the lower fuel filtering portion (42) and such that the coarse apertures (44.sub.O) of the upper bypass portion (44) are distally spaced from the inlet orifice (18.sub.O). The fuel intake device is further characterized by a shroud member (50) disposed about the filter assembly (40), which shroud member (50) includes an upper end portion (52) disposed in sealed combination with an external peripheral surface (18.sub.P) of the internal fuel feed line (18) and a lower end portion (54) which extends into the sump region (26) of the fuel tank (14). The lower end portion (54), furthermore, defines an opening for facilitating fuel flow to the filter assembly (40).

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Orange, CT, United States of America

Scott A Chasen