The Boeing Company

Other

David C Reusch

Marc Rollo Matsen

Aaron William Bartel

Sahrudine Apdalhaliem

Jeffery Lee Marcoe

Waeil M Ashmawi

Adriana Willempje Blom-Schieber

Adriana Willempje Blom

Kevin W Beyer

Angelo Rossi

Jeffrey V Lindstrom

Bradley E Platin

R David Reed

A radius filler includes a plurality of fibers encapsulated in resin and braided into a braided radius filler. The braided radius filler has a substantially triangular shape with concave radius filler side surfaces and a substantially planar radius filler base surface.

Radius filler for composite structure

An aerodynamic structure incorporated in an aircraft control surface provides a spar extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

Kicked spars for rudder and elevator applications

An aerodynamic structure incorporated in an aircraft control surface () provides a spar () extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

The present disclosure is generally directed to a composite trailing edge control surface including a contiguous one-piece composite control surface skin wrapped around a plurality of stiffening cores, a plurality of hinge fittings, and a plurality of substantially parallel ribs. The contiguous one-piece composite control surface skin provides a control surface on opposing sides of the trailing edge control surface and substantially distributes bending, shear and torsion loads of the trailing edge control surface to the plurality of hinge fittings and the plurality of substantially parallel ribs. A method of manufacturing the trailing edge control surface includes positioning a contiguous one-piece composite control surface skin on a substantially flat tool. A plurality of stiffener cores having a plurality of thin covering skins are positioned on the contiguous one-piece composite control surface skin and are cured to create a laminate sandwich composite structure skin that is trimmed and has fastener apertures and hinge fitting access apertures provided there-through.

Structural arrangement and method of fabricating a composite trailing edge control surface

An accurate and compact flap skew detection system that operates independent of the flap-drive system comprises, in a preferred embodiment, three major elements; a rotary position sensor located on fixed wing structure; a push-pull link and crank arm to convert translational flap motion into rotary sensed motion at the sensor; and a computer processing means to process the rotational sensed information and to compute a flap skew algorithm. Inter-flap and intra- flap translational motion is sensed and compared using a plurality of rotary sensors. Sensors falling outside of predetermined limits or violating control law rules indicate a non-synchronous or asymmetrical &ldquo;skewed&rdquo; condition.

Method and apparatus for detecting skew and asymmetry of an airplane flap

A pylon (70) on one structure (68) abuts a side surface of a mounting flange (64) carried by another structure (60) and is bonded thereto by an adhesive layer (76). A flattened tube (78) is positioned between pylon (70) and flange (64). Explosive cords (82) are detonated inside tube (78) to expand tube (78) to a rounded configuration. This causes pylon (70) to peel away from flange (64) and to peel adhesive layer (76) to thereby release structures (60,68) from each other. In another embodiment, a structure (4) has a wall (6) including an outer skin (8), an inner skin (10), and a honeycomb core (12). Outer end portions (14,20) of skins (8,10) form two mounting flanges that are bonded by adhesive layers (40,42) to opposite surfaces of a mounting flange (32) carried by another structure (28). Detonation of explosive cords (50) inside two expandable members ( 46,46') causes skin flanges (14,20) to peel away from flange (32) and peel layers (40,42).

Growing community of inventors

Normandy Park, WA, United States of America

David C Reusch