The Boeing Company

James Frederick Ackermann

Richard Bruce Tanner

Mostafa Rassaian

Omid B Nakhjavani

Shahriar Khosravani

Forouzan Behzadpour

Steven J Burpo

Mohammad Ali Heidari

Ian C Burford

Gregory Robert Gleason

Thomas V Gendzwill

Michael Patterson Johnson

Robert A Rapp

Anthony K Gilbert

Dyrk L Daniels

Joshua A Ross

Brian H Korenga

Ken M Tanino

Christopher C Eastland

A fastening system for aerospace vehicles including a dielectric nut retainer strip formed of dielectric material and having at least one fastener thru hole and at least one cap receiver portion. Also included are an anti-rotation nut retainer portion integrally formed in the dielectric nut retainer adjacent to the at least one fastener thru hole, a cap configured to mate with the at least one cap receiver portion, a fastener covered in a conductive coating, and an anti-rotation nut configured to fit in the anti-rotation nut retainer portion and couple with the fastener.

Apparatus and methods for lightning protection and locating of fastener nuts with dielectric materials

A method and apparatus for forming a seal over a hole in a structure. The apparatus comprises a washer, a sleeve, and a fastener. The washer has a first channel. The sleeve has a second channel and an expandable section. The sleeve is positioned inside the first channel in the washer. The fastener has an elongate portion positioned inside the second channel of the sleeve to cause at least a portion of the expandable section of the sleeve to form a first interference fit with the washer.

Method for fuel tank spark containment

A system and method for creating an optimized composite laminate structure containing a plurality of plies. The system has a processor and a memory, including an application interface. The application interface, when executed by the processor, is configured to operably: receive an input file having one or more of a maximum number of plies, design variables, material properties, and design constraints; determine an initial layup sequence defining parameters of a fiber orientation angle for each ply, and a total percentage of plies at a given fiber orientation angle; iteratively adjust the parameters, until an optimum set of parameters is obtained that achieves one or more predetermined margins of safety, and that achieves optimization of the composite laminate structure; and generate an output file for creating a layup, according to the parameters. The system further has a layup system for creating the optimized composite laminate structure.

System and method for optimizing composite laminate structures

Apparatus for fuel tank spark containment

A method of manufacturing a composite panel is described. The method includes pre-stabilizing a honeycomb core with at least one layer of a pre-stabilizing material, surrounding the honeycomb core with at least one composite laminate skin layer, and curing the at least one composite laminate skin layer.

Composite panel and method of manufacturing the same

An aircraft joint comprises a wing structure and a wing tip. The wing structure has a first part of a clevis and lug fastening system located around an outer end of the wing structure. The wing tip has a second part of the clevis and lug fastening system located around an end of the wing tip. The wing tip is capable of being joined to the outer end of the wing structure. An upper aerodynamic surface and a lower aerodynamic surface are formed by joining the wing structure and the wing tip. The first part and the second part are located about a center between the upper aerodynamic surface and the lower aerodynamic surface. The first part and the second part engage each other such that a moment reaction occurs around the upper aerodynamic surface and the lower aerodynamic surface.

Wing tip joint in airfoils

A wing panel structure for an aerospace vehicle or the like may include an outer layer of material having a predetermined thickness. A core structure may be placed on at least a portion of the outer layer of material. An inner layer of material may be placed at least on the core structure. The inner layer of material may have a selected thickness less than the predetermined thickness of the outer layer of material.

Wing panel structure

Growing community of inventors

Woodinville, WA, United States of America

James Frederick Ackermann