The Boeing Company

Mcdonnell Douglas Corporation

Mcdonnell Douglas Helicopter Company

Brian Koorosh Hamilton

Ahmed A Hassan

Gregory E Dockter

Stephen Lewis Guymon

Terrence S Birchette

Robert R Murrill

Hieu Thien Ngo

Thu N Vu

Murray J Hines

An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.

Composite material for geometric morphing wing

An airfoil member () includes a geometric morphing device (). The geometric morphing device () has an inflatable member (). The inflatable member () has an exterior wall () and multiple inflated states. The exterior wall () includes a layer with one or more fibers embedded therein. The exterior wall () controls size, shape, and expansion ability of the geometric morphing device ().

Fiber matrix for a geometric morphing wing

An airfoil member () is provided including a geometric morphing device (). The geometric morphing device () has an inflatable member (). The inflatable member () has an exterior wall () and multiple inflated states. A fiber mesh () is coupled to at least a portion of the exterior wall () and changes in shape according to fiber angle. Shape and size of the geometric morphing device () are adjustable by changing inflated state of the inflatable member (). An airfoil member altering system () and a method of performing the same are also provided as well as a method of forming the geometric morphing device ().

Geometric morphing wing

An active control device is disclosed comprising an array of actively controlled oscillating air jets disposed on an aircraft structure. In a preferred embodiment, the device senses parameters associated with incipient unsteady aerodynamic excitation, such as free stream gusts, shed wakes in rotor and turbomachinery flows, or oscillatory motion of trailing edge control surfaces such as ailerons. These parameters are provided as input signals to a processor. Based on the input signals, the processor generates output signals that are used to operate the air jet array in a manner counteractive to the unsteady forcing. The air jet array can be used on numerous aircraft structures, including rotor blades, wings, engine inlets, engine exhausts, blunt surfaces and nozzles.

Gust alleviation/flutter suppression device

An airfoil member ( ) is provided including a geometric morphing device ( ). The geometric morphing device ( ) has an inflatable member ( ). The inflatable member ( ) has an exterior wall ( ) and multiple inflated states. Multiple layers are coupled to at least a portion of the exterior wall ( ) and control size, shape, and expansion ability of the geometric morphing device ( ). The geometric morphing device ( ) is adjustable in size and shape by changing inflated state of the inflatable member ( ). An airfoil member altering system ( ) and a method of performing the same are also provided as well as a method of forming the geometric morphing device ( ).

Geometric morphing wing with layers

A geometric morphing wing is provided, including a rigid internal core surrounded by an expandable spar and covered by a wing surface overlay . The expandable spar includes an elastomeric bladder movable between a non-inflated state and an inflated state such that the airfoil shape of the geometric morphing wing is adjusted.

Geometric morphing wing with expandable spars

A composite member having increased resistance to delamination includes a reinforcing wrap of fiber-matrix composite material which is encircled about the member so that the edge surfaces of the member are covered by the wrap. The wrap includes fibers which are oriented from about &minus;60&deg; to about &plus;60&deg; relative to the direction along which the reinforcing wrap is wrapped about the member. The fibers of the reinforcing wrap impart increased third-axis or Z-direction strength at the edges of the member where interlaminar tensile stresses are greatest.

Composite member having increased resistance to delamination and method of making same

The present invention relates to an improved helicopter rotor system including a contoured flexure strap having a simplified geometrical configuration. The flexure strap serves to join the rotary hub assembly with the rotor blades and is formed of fiberglass. The primary load carrying fibers of the flexure strap preferably extend in the same direction as the spanwise axis of the flexure strap in order to withstand the centrifugal forces acting on the strap. The inboard end portion of the flexure strap includes two separate ends, with one of the ends extending in a vertically upward direction and the other end in a vertically downward direction. This allows the ends of flexure straps positioned on opposite sides of the rotary hub assembly to overlap one another and be retained in place by a single pin and bolt assembly. A cloth wrap of composite matrix material surrounds portions of the flexure strap to provide redundancy which prevents the fibers in the flexure strap from delamination when subjected to forces arising during operation of the helicopter.

Growing community of inventors

Mesa, AZ, United States of America

Brian Koorosh Hamilton