The Boeing Company

Waeil M Ashmawi

Sahrudine Apdalhaliem

Moushumi Shome

Jeffery Lee Marcoe

Marc Rollo Matsen

Jaime C Garcia

Kimberly Dawn Meredith

Kay Youngdahl Blohowiak

Frederick Theodore Calkins

Brett Ian Lyons

Adriana Willempje Blom

Forouzan Behzadpour

John B Moser

Morteza Safai

Aaron William Bartel

Adriana Willempje Blom-Schieber

David C Reusch

Angelo Rossi

Heh-Chyun Cliff Chen

Zayd I Abdel-Kamel

Muhammad Mustajab Malik

Janet Mary Layng

A thin, lightweight control surface is fabricated by induction consolidation of thermoplastic components. The control surface includes a forward section co-consolidated with a rear section. The front section includes a cover and the rear section includes a truss core covered by an outer skin.

Method of making a control surface

Examples are disclosed herein that relate to vehicles, composite parts, and three-dimensional (3D) textile preforms for composite parts. In one example, a 3D textile preform for a composite part comprises a flange portion and a stiffener portion extending upwardly from the flange portion. The stiffener portion comprises a first wall portion that extends from the flange portion and a second wall portion that extends from the flange portion at a location spaced from the first wall portion. A connecting portion connects the first wall portion and the second wall portion at a location spaced from the flange portion.

Three-dimensional textile preforms and composite parts comprising textile preforms

Stiffened skin panels comprise alternating truss core portions and solid laminate portions sandwiched between inner and outer facesheets, all formed from a fiber reinforced thermoplastic. The components of the panels are co-consolidated using induction heating. The panels are stiffened with spars fastened to the solid laminate portions.

Thermoplastic skin panels, torque box and method

A support structure to mount landing gear to a wing spar of an aircraft. The support structure includes a trunnion assembly having a first trunnion and a second trunnion that are connected together with the first trunnion positioned on a first side of the wing spar and a second trunnion positioned on an opposing second side of the wing spar. The trunnion assembly is configured to support a first section of the landing gear.

Support structure for an aircraft landing gear

Described herein are stringer assemblies, such as blade stringers, and methods of forming thereof. A stringer assembly comprises a first fabric composite stiffener, a second fabric composite stiffener, and an intermediate tape composite stiffener, disposed between and connected to each of the first and second stiffeners. Using three separate components allows forming sharp bends, eliminating voids and gap fillers, and adding new features, such as edge reinforcements. Each of the first and second fabric composite stiffeners comprises a web portion, a flange portion, and a curved portion, positioned between the web and flange portions. The web portions surround and are attached to the intermediate tape composite stiffener and, in some examples, include tapered-out edges for additional rigidity. The flange portions are attached to the composite base. The curved portions conform to the flared-out edges of the intermediate tape composite stiffener, which extends and connects to the composite base.

Stringer assemblies and methods of forming thereof

A movable surface of an aircraft has a front spar extending along a spanwise direction between opposing movable surface ends. The movable surface also includes a plurality of ribs defining a plurality of bays between adjacent pairs of the ribs. Each rib extends between the front spar and a trailing edge portion of the movable surface. The movable surface further includes an upper and a lower skin panels coupled to the ribs and the front spar. In addition, the bull surface includes a plurality of bead stiffeners coupled to an inner surface of at least one of the upper skin panel and the lower skin panel. The bead stiffeners within the bays are spaced apart from each other and are oriented non-parallel to the front spar and have a bead stiffener cap having opposing cap ends respectively locate proximate the front spar and the trailing edge portion.

Bead-stiffened movable surfaces

A window clamp system and method are to secure a window pane to a window frame of a vehicle. The window clamp system includes a mounting bracket configured to be secured to the window frame, one or more ratchets coupled to the mounting bracket, and a spring clip configured to move in relation to the mounting bracket and the one or more ratchets. The spring clip is configured to engage a seal positioned around the window pane.

Window clamp system for a vehicle

A computer-implemented method of determining moisture content of a composite structure is provided. The method includes performing a thermal analysis calculation on the composite structure to determine a temporal surface temperature profile of the composite structure based on temporal environmental parameter profiles, wherein the surface temperature profile is determined independently of a moisture content of the composite structure. The method also includes performing a moisture content analysis calculation on the composite structure to determine a moisture content of the composite structure, wherein the moisture content analysis calculation is based on the determined temporal surface temperature profile and a thickness of the composite structure. The thermal analysis calculation is performed iteratively with a first time period and the moisture content analysis calculation is performed iteratively with a second time period that is longer than the first time period.

Methods and systems for designing a composite structure

Provided are assemblies having composite structures interlocked with shape memory alloy structures and methods of fabricating such assemblies. Interlocking may involve inserting an interlocking protrusion of a shape memory alloy structure into an interlocking opening of a composite structure and heating at least this protrusion of the shape memory alloy structure to activate the alloy and change the shape of the protrusion. This shape change engages the protrusion in the opening such that the protrusion cannot be removed from the opening. The shape memory alloy structure may be specifically trained prior to forming an assembly using a combination of thermal cycling and deformation to achieve specific pre-activation and post-activation shapes. The pre-activation shape allows inserting the interlocking protrusion into the opening, while the post-activation shape engages the interlocking protrusion within the opening. As such, activation of the shape memory alloy interlocks the two structures.

Assemblies including shape memory alloy fittings and composite structural members

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

Manufacturing a thermoplastic composite tubular structure embedded with a first load fitting comprising the steps of braiding a first plurality of inner layers of thermoplastic composite material around a soluble, expandable mandrel. A first load fitting is positioned on the first plurality of inner layers of thermoplastic composite material. A second plurality of outer layers of thermoplastic composite material is braided around the first load fitting and the mandrel so as to form an overbraided mandrel embedded with the first load fitting. The overbraided mandrel is installed into a matched tooling assembly and heated at a specified heating profile in order to consolidate the first plurality of inner layers of thermoplastic composite material and the second plurality of outer layers of thermoplastic composite material with the first load fitting so as to form a thermoplastic composite tubular structure embedded with the first load fitting. A second load fitting may be positioned on the first plurality of inner layers of thermoplastic composite material.

Thermoplastic composite structures embedded with at least one load fitting and methods of manufacturing same

A system and method for harvesting energy from a vehicle, e.g., an aircraft, in operation. A plurality of piezoelectric members are coupled between structural members in the vehicle. A first portion of the plurality of piezoelectric members are non-resonant piezoelectric spacers coupled between structural members subject to a constant load during operation of the vehicle. A second portion of the plurality of piezoelectric members are resonant piezoelectric fillers coupled between structural members subject to a cyclical load during operation of the vehicle. Electrical conversion circuitry is coupled to each of the plurality of piezoelectric members for converting the output of each piezoelectric member to usable electrical energy. The electrical conversion circuitry is coupled to an energy storage device for storing the usable electrical energy and/or to an interface circuit for supplying energy for use in an electrical system in the vehicle.

System and method for harvesting energy from a moving vehicle

Methods and apparatuses are disclosed relating to multilayer 3D textile composite materials containing self-healing resins for use as protective structures on stationary objects, and moving objects including, without limitation, vehicles including spacecraft and aircraft.

Self-repair structures and methods for making the same

In one or more aspects of the present disclosure, a mandrel is disclosed. The mandrel having a shape memory alloy (SMA) shell having a longitudinal axis, an interior extending along the longitudinal axis and an exterior contour, the SMA shell being configured to interface with a structure to be cured, and at least one SMA actuation member disposed within the interior and connected to the SMA shell, where the at least one SMA actuation member is configured to exert pressure against the SMA shell effecting an interface pressure between the exterior contour of the SMA shell and the structure to be cured where the exterior contour has a predetermined actuated shape that corresponds to a predetermined cured shape of the structure to be cured.

Apparatus and method for a shape memory alloy mandrel

A method of bonding materials may comprise defining a bond interface between two materials in a cure zone on a surface of an object, and non-conductively heating the bond interface without directly heating the surface outside of the cure zone. Non-conductively heating the bond interface may involve applying microwave radiation to the bond interface.

Growing community of inventors

Bellevue, WA, United States of America

Waeil M Ashmawi