Abstract: A coupling system and method are configured to secure one or more spars of a wing of an aircraft to one or more struts. The coupling system and method include a plurality of interface joints that secure the one or more spars to the one or more struts. At least a portion of a front surface of the one or more spars is linearly aligned with at least a portion of a rear surface of the one more struts.

Abstract: A coupling system and method are configured to secure one or more spars of a wing of an aircraft to one or more struts. The coupling system and method include a plurality of interface joints that secure the one or more spars to the one or more struts. At least a portion of a front surface of the one or more spars is linearly aligned with at least a portion of a rear surface of the one more struts.

Abstract: A coupling system is configured to secure one or more struts to a wing of an aircraft. The coupling system includes one or more splice straps that secure the one or more struts to the wing. A method for securing one or more struts to a wing of an aircraft includes securing, by one or more splice straps, the one or more struts to the wing.

Abstract: A strut assembly for coupling an engine to a wing of an aircraft, the strut assembly comprising a mid truss assembly comprising a fore portion and an aft portion; an engine mount member connected to the fore portion of the mid truss assembly; an aft truss assembly comprising a fore portion and an aft portion, the fore portion of the aft truss assembly being connected to the aft portion of the mid truss assembly; an aft strut bulkhead connected to the aft portion of the aft truss assembly; and a wing mounting feature operatively connected to, and located aft of, the aft strut bulkhead.

Abstract: An engine attachment system includes a strut box. The strut box includes a longitudinal axis, a forward portion that extends along the longitudinal axis, and an aft portion that extends from the forward portion along the longitudinal axis. The engine attachment system includes a forward attachment apparatus that is coupled to the forward portion of the strut box and that is coupleable to a forward spar of the wing. The engine attachment system includes an aft attachment apparatus that is coupled to the aft portion of the strut box and that is coupleable to an aft spar of the wing. When the strut box is coupled to the wing by the forward attachment apparatus and the aft attachment apparatus, the aft portion of the strut box is positioned under the wing. The strut box is coupleable to an engine.

Abstract: A method includes determining, at a processor, whether a number of points of drawing data associated with a part satisfies a threshold. The method further includes identifying the drawing data as validated geometry data when the number of points satisfies the threshold.

Abstract: An apparatus for mounting an aircraft engine to a wing includes a torque box strut for supporting the engine and a mounting system for attaching the torque box strut to the wing. The mounting system has an aft mounting system for attaching the torque box strut to the wing and that has at least one active aft link for attaching the torque box strut to the wing during normal aircraft operation, and at least one aft link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active aft link. The mounting system has a forward mounting system for attaching the torque box strut to the wing and that has at least one active forward link for attaching the torque box strut to the wing during normal aircraft operation, and at least one forward link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active forward link.

Abstract: A method includes determining, at a processor, whether a number of points of drawing data associated with a part satisfies a threshold. The method further includes identifying the drawing data as validated geometry data when the number of points satisfies the threshold.

Abstract: In an embodiment, a drawing file and an interface application are activated. Geometry data is extracted from the drawing file with the interface application. In another embodiment, contents of a geometry file can be automatically read into a drawing application to create a drawing file. Contents of the geometry data file may be revised before being read. In another embodiment, a finite element model can be generated. A control file for an item to be modeled is selected. Contents of the selected control file and part geometry data files identified in the selected control file are read. A finite element model for each part is generated simultaneously from all of the part geometry data files. When more than one part geometry data files are identified in the control file, all of the finite element models of the parts can be integrated into a finite element model of a product.

Abstract: An apparatus for mounting an aircraft engine to a wing includes a torque box strut for supporting the engine and a mounting system for attaching the torque box strut to the wing. The mounting system has an aft mounting system for attaching the torque box strut to the wing and that has at least one active aft link for attaching the torque box strut to the wing during normal aircraft operation, and at least one aft link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active aft link. The mounting system has a forward mounting system for attaching the torque box strut to the wing and that has at least one active forward link for attaching the torque box strut to the wing during normal aircraft operation, and at least one forward link catcher for attaching the torque box strut to the wing upon a failure of one of the at least one active forward link.

Abstract: Aircraft engine nacelles and methods for structurally attaching them to aircraft structures, such as aircraft wings. In one embodiment, an aircraft engine nacelle is attached to a wing between a trailing edge region of the wing and an aft deck region of the wing. In one aspect of this embodiment, the engine nacelle includes a forward portion having first and second structural attach points offset from each other in a first direction at least generally perpendicular to a central axis of the engine nacelle. The first and second structural attach points can be configured to fixedly attach the engine nacelle to the wing at least proximate to the trailing edge region. In another aspect of this embodiment, the engine nacelle includes a side portion having at least a third structural attach point offset from the first and second structural attach points in a second direction at least generally parallel to the central axis.

Abstract: Aircraft engine nacelles and methods for structurally attaching them to aircraft structures, such as aircraft wings. In one embodiment, an aircraft engine nacelle is attached to a wing between a trailing edge region of the wing and an aft deck region of the wing. In one aspect of this embodiment, the engine nacelle includes a forward portion having first and second structural attach points offset from each other in a first direction at least generally perpendicular to a central axis of the engine nacelle. The first and second structural attach points can be configured to fixedly attach the engine nacelle to the wing at least proximate to the trailing edge region. In another aspect of this embodiment, the engine nacelle includes a side portion having at least a third structural attach point offset from the first and second structural attach points in a second direction at least generally parallel to the central axis.

Abstract: A system and method for automatically and rapidly generating a finite element model of a component are provided. A two-dimensional diagram of points and lines that represent geometry of a component is input. A first input file is created from the two-dimensional diagram. The first input file defines geometrical structure of the component. A second input file is created that defines properties and materials of the component. The properties and materials are defined responsive to the geometrical structure of the component, and are defined according to a predetermined set of properties and materials rules for the component. Without any surfaces being generated to define geometrical structure of the component, a finite element model of the component is generated from the defined geometrical structure of the component and the defined properties and materials of the component.

Abstract: An aircraft assembly includes a wing, a pylon structure attached to the wing, an aft engine mount attached to the pylon structure, and an engine attached to the aft engine mount. The aft engine mount includes a pivotal attachment to the pylon structure and first and second spring beams operatively connected to the pylon structure at opposing sides of the pivotal attachment for damping pivotal movement of the engine with respect to the pylon structure to enable tuning of the natural frequency of the engine to avoid wing flutter.

Abstract: An improved strut wing interface having dual upper links which lie along parallel planes or in diverging planes. Various design enhancements and capabilities are achieved when using the dual upper links as opposed to a conventional single upper link.