Textron Innovations Inc.

Bell Helicopter Textron Inc.

Bell Textron Inc.

Bell Helicopter Rhode Island Inc.

Bell Helicopter Innovations

Michael Dean Dearman

Michael Christopher Burnett

Wei-Yueh Lee

Amarjit Olenchery Kizhakkepat

Ken Shundo

Tyler Wayne Baldwin

Glenn Alan Shimek

Paul K Oldroyd

Kyle Thomas Cravener

Jared Mark Paulson

Paul Branson Sherrill

Mark Adam Wiinikka

Terry K Thompson

Nicholas Allen Torske

Wei-Yeuh Lee

A method for forming composite components includes disposing composite laminate over a mandrel. The method further includes infusing the composite laminate with a resin. A gelation of the infused resin is caused by applying a first environmental condition to the composite laminate and mandrel. At least a portion of the mandrel is deformed by applying a second environmental condition to the composite laminate and mandrel. The method further includes forming a composite structure by curing the composite laminate infused with resin. The deformed mandrel is removed from the composite structure after forming the composite structure.

Methods and systems for manufacturing composite components

An anti-aircraft system is described and includes an unmanned aerial vehicle (UAV) comprising a body; a wing connected to the body; and propulsion systems associated with the wing, wherein the propulsion systems comprise pylons releasably connected to opposite ends of the wing such that the propulsion systems may be selectively released from the wing during flight of the UAV.

Unmanned aerial vehicle for anti-aircraft applications

A method of offset load testing a tubular composite specimen with two pairs of aligned holes and having at least one defect, the method comprising: providing a testing apparatus having a pair of arms including a fixed arm and a mobile arm; securing the pair of arms using a fastener assembly in each of the two pairs of aligned holes; and moving the mobile arm to impart an offset load force to the tubular specimen. One aspect includes a method of offset load testing comprising: providing a testing apparatus having a pair of arms including a fixed arm and a mobile arm; providing a tubular composite specimen with a top portion and a bottom portion; securing the pair of arms to the top and bottom portions of the tubular composite specimen; and moving the mobile arm to impart an offset load force to the tubular composite specimen.

Methods of making a tubular specimen with a predetermined wrinkle defect

In an aspect, there is a method of determining allowable defects for a composite component comprising identifying at least one wrinkle characteristic of a composite component wrinkle defect; making a first plurality of specimens each having a predetermined wrinkle defect representative of the composite component wrinkle defect; measuring each of the predetermined wrinkle defects in the first plurality of specimens for at least one performance metric to generate performance data; and generating an allowable wrinkle defect profile based on the performance data from the first plurality of specimens. In other aspects, there are methods of making a specimen with a predetermined wrinkle defect.

Methods of making a specimen with a predetermined wrinkle defect

A tiltrotor controls shield having a blade or wire substructure under a fragile spinner fairing improves bird strike durability. The present disclosure discloses a spinner wind fairing with a shield structure disposed thereunder for providing protection to the proprotor assembly components. The shield structure can segment a projectile, such as a bird, that penetrates the spinner fairing into a series of smaller and lower energy elements spread across a wider area, such that the rotor components can withstand the impact of the smaller elements without damage.

Tiltrotor controls shield

A light weight hybrid torque transfer joint trunnion has an integral metal hub spline fitting oriented on a center axis. This integral metal hub spline fitting may be made of steel, aluminum, titanium, or the like and may be generally cylindrical. The integral metal hub spline fitting defines an integral central internally-splined mast or driveshaft coupling opening centered about the center axis. A composite material body centrally retains, and is cured to, the metal hub spline fitting. Torque transfer joint link attachment pins extend from the composite material body and are rigidly linked to the metal hub spline fitting. In an example constant-velocity joint, a plurality of pivoting linkages may each be rotatably coupled to the torque transfer joint link attachment pins, and each of the plurality of pivoting linkages may, in turn be secured to a rotor yoke configured to mount a plurality of rotorcraft blades.

Hybrid light weight rotorcraft hub trunnions

An example rotating swashplate ring to rotor mast connection includes a polygon-shaped drive tube secured to the rotor mast and a gimbal joint connected between the rotating swashplate ring and the polygon-shaped drive tube, wherein the gimbal joint rotates with the rotor mast and can translate axially along the polygon-shaped drive tube.

Rotating swashplate ring to rotor mast connection

An ice-management method for an aircraft includes scavenging torque from a mast of the aircraft with a system that is configured to provide an ice-management capability. The method includes using the scavenged torque to impart a vibratory force to an arm of the system and imparting the vibratory force from the arm to an inner surface of a spinner of the aircraft via a contact of the arm.

Scavenged-power ice-management system and method for an aircraft

In a first aspect, there is a method of making a specimen with a predetermined wrinkle defect, the steps including orienting a composite material around a layup tool at a wrap angle to form a closed loop; and generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of determining allowable defects for a composite component.

There is a method of making a tubular specimen with a predetermined wrinkle defect including providing a layup tool with a cavity forming member having a cavity which resembles a desired shape of the at least one wrinkle; orienting a composite material around the mandrel at a wrap angle to form a closed loop; positioning a wrinkle tool on the closed loop; and/or generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a tubular specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of offset load testing a tubular composite specimen. In a third aspect, there is a method of determining allowable defects for a composite component.

A bearing assembly for coupling a proprotor blade to a yoke in a proprotor system. The bearing assembly is positionable within an inboard pocket of a blade arm of the yoke. The proprotor system is operable for use on a tiltrotor aircraft having helicopter and airplane flight modes. The bearing assembly includes a centrifugal force bearing and a shear bearing having an inboard beam coupled therebetween. The centrifugal force bearing has a mating surface, a lateral movement constraint feature and at least one radially extending anti-rotation feature. The inboard beam has a mating surface in a contact relationship with the mating surface of the centrifugal force bearing, a lateral movement constraint feature operably associated with the lateral movement constraint feature of the centrifugal force bearing and at least one radially extending anti-rotation feature that corresponds with the at least one radially extending anti-rotation feature of the centrifugal force bearing.

Inboard bearing assemblies with anti-rotation features

A proprotor system for a tiltrotor aircraft includes a yoke having a plurality of blade arms each having an inboard pocket. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets. Each of a plurality of inboard beams is disposed at least partially between a centrifugal force bearing and a shear bearing of each bearing assembly and has a proprotor blade coupled thereto. Each of a plurality of latch assemblies selectively couples one of the bearing assemblies to the yoke. Each latch assembly is rotatable relative to the yoke between an engaged position wherein the latch assembly is engagable with one of the bearing assemblies to couple the bearing assembly to the yoke and a disengaged position wherein the latch assembly is disengaged from the respective bearing assembly enabling installation and removal of the respective bearing assembly relative to the respective pocket.

Inboard bearing assemblies with improved accessibility

A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode includes a yoke having a plurality of blade arms each having an inboard pocket with a load transfer surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets. Each of a plurality of inboard beams is disposed at least partially between a centrifugal force bearing and a shear bearing of each bearing assembly and has a proprotor blade coupled thereto. Each of a plurality of independent shoes is coupled between one of the centrifugal force bearings and the yoke. Each shoe has a load transfer surface that has a contact relationship with the load transfer surface of the respective inboard pocket forming a centrifugal force load path therebetween.

Inboard bearing assemblies having independent shoes

A spinner mounted gun system includes a receiver and a barrel connected to a mast of a rotorcraft.

Growing community of inventors

Fort Worth, TX, United States of America

Michael Dean Dearman