The Boeing Company

Alpha 1 Engineering Technology Group, Inc.

Alphal Engineering Technology Group, Inc.

Dan-jumbo, Eugene

Eugene Dan-Jumbo

Russell Lee Keller

Everett A Westerman

Joel Patrick Baldwin

Richard M Sutherland

In an embodiment, a material includes at least one outer section and a midsection attached to the outer section. The midsection includes a first antimicrobial membrane patch layer configured to contact a body, a second antimicrobial membrane patch layer disposed adjacent to the first antimicrobial patch layer, and an air gap disposed between the first patch and second antimicrobial patch layers. The first and second antimicrobial patch layers each are formed from respective balanced warp tows and fill tows in a plain-weave pattern, and each layer include copper filaments disposed in a plurality of the tows, each of the copper filaments including at least Cu+ or Cu+++ ions. Such a material may be suitable for notification and protection of a body from a soil deposited on the material.

Anti-microbial device and process therefore

In an embodiment, a garment, such as a smart pull-up, includes at least one outer section and a midsection attached to the outer section. The midsection includes a first antimicrobial membrane patch layer configured to contact a wearer's body, a second antimicrobial membrane patch layer disposed adjacent to the first antimicrobial patch layer, and an air gap disposed between the first patch and second antimicrobial patch layers. The first and second antimicrobial patch layers each are formed from respective balanced warp big tows and fill tows in a plain-weave pattern, and each layer include copper filaments disposed in a plurality of the tows, each of the copper filaments including at least Cu+/Cu+++ ions. Such a smart pull-up may be suitable for either adult who cannot use the toilet, or child, or healthy adult and, therefore, may urinate and defecate himself/herself.

Anti-microbial balanced weave wearable undergarment and process therefore

An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment.

Bonded and tailorable composite assembly

In an embodiment, a garment, such as a smart pull-up, includes at least one outer section and a midsection attached to the outer section. The midsection includes a first antimicrobial membrane patch layer configured to contact a wearer's body, a second antimicrobial membrane patch layer disposed adjacent to the first antimicrobial patch layer, and an air gap disposed between the first patch and second antimicrobial patch layers. The first and second antimicrobial patch layers each are formed from respective balanced warp big tows and fill tows in a plain-weave pattern, and each layer include copper filaments disposed in a plurality of the tows, each of the copper filaments including at least Cu/Cuions. Such a smart pull-up may be suitable for either adult who cannot use the toilet, or child, or healthy adult and, therefore, may urinate and defecate himself/herself.

A patch for a structure has a rework area with an inconsistency formed therein. The patch comprises a patch body having at least two regions including a fail-safe region and a safe-life region encompassing the fail-safe region. The safe-life region has a mode I interlaminar fracture toughness that is less than the mode I interlaminar fracture toughness of the fail-safe region.

Oblong configuration for bonded patch

Apparatus and methods to determine structural integrity of composites are described herein. One described example method for determining sufficiency of structural integration of a composite structure for an aircraft includes applying a fluid droplet to a surface of the composite structure, determining a three-dimensional contact angle between the surface and a portion of the droplet, comparing the three-dimensional contact angle to a threshold angle, and determining whether the structural integration of the composite structure is sufficient based on the comparison.

Methods and apparatus to determine integrity of composite structures

A method and apparatus for reworking a composite structure. A composite rework patch system comprises a composite rework patch and a plurality of adhesive layers. The composite rework patch includes a first side having a contour conforming to an inconsistent area on the composite structure. The composite re patch comprises a plurality of regions having different structural properties. The plurality of adhesive layers is on the first side of the composite rework patch. The plurality of adhesive layers change in thickness within at least one region of the composite rework patch to form tapered adhesive sections.

Structural bonded patch with tapered adhesive design

A system for repair of damaged holes in composite structures incorporates a repair system tool device having a sleeve sized to be closely received in a hole in a composite structure. The sleeve has a central bore for receiving parent resin and an array of orifices for radial expulsion of the parent resin into the hole. A caul plate seals the central bore and a vacuum bag covering the caul plate is sealed to the surface of the composite structure. Introduction of vacuum in the vacuum bag provides a differential pressure for infusion of resin from the orifices in the sleeve into delaminations extending from the hole.

Structural integrated repair method and system tool device for repairing delaminated composite structures

A composite laminate patch for reworking an inconsistent area in a structure has inner and outer control regions possessing differing interlaminar fracture toughnesses for controlling the advance of a disbond in the patch. One or more separation zones in the patch between the control regions aids in diffusing the fracture energy of the disbond as the disbond advances from the inner region to the outer region.

Bonded patch having multiple zones of fracture toughness

A repair patch for reworking an inconsistent area of a composite structure includes a patch body adapted to cover the inconsistent area and having a first patch region, a second patch region outside the first patch region and a first separation zone between the first patch region and the second patch region, with the first patch region, the first separation zone and the second patch region having increasing interlaminar fracture toughness from a center to an edge of the patch body; and a layer of adhesive for bonding the patch body to the composite structure.

Discretely tailored multi-zone bondline for fail-safe structural repair

A bond surface testing apparatus and method are presented. The bond surface testing apparatus comprises a solution chamber; a plurality of solution containers located in the solution chamber; a plurality of microfluidic pipettes; and an information capture module. Each solution container in the plurality of solution containers includes a microfluidic pipette in the plurality of microfluidic pipettes. A number of the plurality of microfluidic pipettes has a non-circular cross-section. The information capture module is physically associated with the solution chamber and is configured to capture information relating to bonding surface properties of the bonding surface.

Bond surface testing apparatus and method

A composite rework patch and method. The composite rework patch comprises a trapezoidal shape, a first region, and a second region. The trapezoidal has a first base and a second base, the first base parallel to the second base. The first region comprises a first composite material portion and a first adhesive portion. The second region comprises a second composite material portion and a second adhesive portion.

Trapezoidal rework patch

The present disclosure relates to a system for testing the strength of a bonded joint between at least two components, wherein the system includes at least one element force energizer that creates an actual mechanical stress in the bonded joint when actuated, wherein the element force energizer is coupled with the at least two components. The system further includes an energy interface that is connectable to a power source, the energy interface being in electrical communication with the at least one element force energizer, and a sensor that detects the actual mechanical stress or strain in the bonded joint. The system may also include a recording device that records and/or transmits the detected mechanical stress or strain in the bonded joint. In one example, the element force energizers include piezoelectric materials.

Apparatus, system, and method for in situ strength testing of a bonded joint

There is provided a high temperature hybridized molecular functional group adhesion barrier coating for a composite structure. The coating has one or more hybridized molecular functional groups attached to a composite surface of the composite structure, wherein the one or more hybridized molecular functional groups are hybridized through a chemical derivatization process. The coating further has one or more chemical derivatization compounds attached to the one or more hybridized molecular functional groups via a condensation reaction. The coating is resistant to high heat temperatures in a range of from about 350 degrees Fahrenheit to about 2000 degrees Fahrenheit, and the coating is a thermally protective, toughened adhesion coating that mitigates effects of a hostile operating environment.

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Bothell, WA, United States of America

Eugene Dan-Jumbo