The Boeing Company

Jeffrey P Baucum

David Mitchell Anderson

John Ralph Hull

Vyacheslav Khozikov

Stephen Roger Amorosi

Gerardo Pena

Mark A Barr

David M Anderson

Jeffrey B Gavin

Dennis Chin

A ice protection system for a truss-braced wing of an aircraft is disclosed. The system includes a wing, a support strut, a joint coupling the support strut to the wing to form a structural truss of the truss-braced wing, a magnetic susceptor disposed on or within the joint, and an induction heating coil disposed on or within the truss-braced wing. The induction heating coil is configured to generate eddy currents inside the magnetic susceptor based on being driven with an alternating current (AC) excitation current. The eddy currents circulate through the magnetic susceptor causing joule heating of the magnetic susceptor to inhibit ice accumulation on the joint.

Ice protection system for a truss-braced wing of an aircraft

Methods, systems, and apparatuses are disclosed for the manufacture of composite components having incorporated reinforcing structures machined into composite material substrates, and composite components manufactured according to disclosed methods, and assemblies and larger structures comprising the composite material components.

Integrally stiffened bonded panel with vented pockets and methods of manufacture

Integrally stiffened bonded panel with machined pockets and methods of manufacture

A method of analyzing a structure includes producing a finite element model of the structure having fibers embedded therein, and including one or more plies. This may include performing a discretization of a digital model of the structure in which each ply of the one or more plies is represented by a mesh of finite elements aligned with a direction of uni-directional fibers embedded in the ply. Producing the finite element model may also include adding a fiber-aligned intraply interface element between selected adjacent finite elements in the mesh of each ply to capture potential intraply failure modes. And the method may include performing a finite element method (FEM) failure analysis of the finite element model under a load, with the FEM failure analysis producing an output that indicates an extent of any of the potential intraply failure modes that result from the finite element model under the load.

Analysis of a structure modeled with intraply interface elements

An aircraft wing slat is formed from composite materials using lay-up and vacuum bagging techniques. The slat lay-up comprises a central honeycomb core sandwiched between upper and lower composite skins, a pre-cured spar and pre-cured stiffeners. After the lay-up is cured and removed from a lay-up mold, leading edge strengthening ribs and a preformed composite nose skin are installed to complete the slat.

Composite wing slat for aircraft

An apparatus for an airplane or other equipment is provided. The apparatus may comprise a multitude of connected arms which are adapted to rotate relative to one another. One end of the apparatus may be connected to a fixed wing, while another end of the apparatus may be connected to a moving slat. The apparatus may be used to deliver conduit from the fixed wing to the moving slat. The conduit may comprise one or more of an electrical de-icing wire, a sensor wire, a control wire, a fiber optic line, and a pneumatic line. Within an internal pathway of the apparatus, the conduit may be freely looped around a curved surface at least one-half turn and fixedly secured to a linear surface. Methods of use and assembly are also provided.

Growing community of inventors

Sammamish, WA, United States of America

Jeffrey P Baucum