Cornerstone Research Group, Inc.

Spirit Aerosystems, Inc.

Bryan Michael Pelley

Joseph H Althaus

Kristin M Cable

Jason Michael Hermiller

Christopher Douglas Hemmelgarn

Matthew Brian Sunday

Jason P Rice

Mitchell D Bauer

Kelly H Ridout

David Ernest Havens

Steven Fillmore Hanson

Brandon Charles Kirby

Jeffrey W Priest

Carl Ray Fiegenbaum

Joshua E Nieman

Joel James Everhart

Ben Dietsch

Cory Kays

S Alan Spring

Karl Gruenberg

Chris D Hemmelgarn

Jennifer M Fries

Methods of making a composite aircraft primary structure include selecting a compression moldable composite sheet molding compound; preparing a first and a second layup with the compression moldable composite sheet molding compound to form a first and a second 3D preform; and compression molding the first and the second 3D preforms to form a first and a second component part. Further, the first component part comprises first geometric joint features, the second component part comprises second geometric joint features, and the second geometric joint features are complementary to the first geometric joint features such that the second geometric joint features are configured to mate with the first geometric joint features. The method further includes assembling the aircraft primary structure by joining the first component part with the second component part by aligning and mating the first geometric joint features and the second geometric joint features; and securing the same.

Method of making composite aircraft primary structures

An aircraft wing and propulsion system includes a leading-edge device positioned at the leading edge of an aircraft wing and one or more propulsors affixed to the main body of the aircraft wing. The leading-edge device includes a moveable slat affixed to the aircraft wing with an extension mechanism such that the moveable slat is translatable between a closed position abutting a main body of the aircraft wing and an open position extended from the main body of the aircraft wing to form a gap. An associated method of operating the same during takeoff and landing includes extending the moveable slat to expose the propulsors on the aircraft wing and operating the propulsors during take-off or landing of the aircraft to provide increased power and lift for the aircraft.

Aircraft wing and propulsion system

Human stabilization platforms may include a support structure configured to rigidly support a person. A rail may extend longitudinally from proximate a portion of the support structure configured to receive the person's head thereon to proximate a portion of the support structure configured to receive the person's lower legs thereon on each lateral side of the support structure. Each rail may include selectable attachment structures distributed along at least a portion of the longitudinal length of the rail. The selectable attachment structures may be configured to receive modular accessories to be secured to the human stabilization platform. The selectable attachment structures may include a channel including alternating enlarged sections and constricted sections.

Human stabilization platforms and related methods

Human stabilization platforms may include a support structure configured to rigidly support a person. A rail may extend longitudinally from proximate a portion of the support structure configured to receive the person's head thereon to proximate a portion of the support structure configured to receive the person's lower legs thereon on each lateral side of the support structure. Each rail may include selectable attachment structures distributed along at least a portion of the longitudinal length of the rail. The selectable attachment structures may be configured to receive modular accessories to be secured to the human stabilization platform. A handle may be located at each end of each rail, each handle being rotatable with respect to the rail. Each handle may be configured to enable manual handling and transport of the human stabilization platform.

Embodiments of an aerodynamic structural insert frame comprise a leading edge, a trailing edge opposite the leading edge, and at least one cavity between the leading edge and trailing edge, wherein the aerodynamic structural insert frame is configured to deflect upon activation by an external stimulus; at least one deformable buckling member extending the distance between opposite edges of the cavity, wherein the deflection of the aerodynamic structural insert frame is configured to trigger deflection of the deformable buckling member; a pivot region; and at least one stopper bar attached to and extending from one edge of the cavity a distance less than the distance between opposite edges of the cavity, wherein the stopper bar is configured to stop the deflection of the aerodynamic structural insert and the buckling member when the stopper bar strikes an opposite edge of the cavity.

Passive adaptive structures

The design of a high efficiency, variable performance vaneaxial fan, requires the utilization of typical fan and single stage compressor design methodologies. To be able to replace multiple fans, the variable vaneaxial fan design must be capable of operation at several different flow rates and total pressures. These operation points can be met by varying motor revolutions per minute (RPM) or geometric parameters such as the hub diameter, tip diameter, as well as blade geometry including number of blades, pitch, spacing, and length. An ideal design with variable performance can replace a family of current fan designs by providing the capability for efficient operation over a range of flow rates and total pressures. This level of variability would not only allow the fan to respond to changing environmental conditions but also to be fit into systems with different characteristics.

Variable performance vaneaxial fan with high efficiency

A method and support apparatus for providing structural support to a mold or mandrel, such as a shape memory polymer (SMP) apparatus configured for shaping a composite part. The support apparatus may comprise a rigid structural member and a plurality of SMP cells attached thereto and configured to inflate or deploy in a malleable state toward and against a surface of the SMP apparatus, mold, or mandrel. Then the SMP cells may be returned to a rigid state while still pressed against this surface, thereby providing structural support when composite material is applied to an opposite surface of the SMP apparatus, mold, or mandrel. After the composite material is cured into the finished composite part, the SMP cells may be deflated or otherwise collapse toward the structural member to provide enough clearance to be removed from the cured composite part.

Reconfigurable shape memory polymer tooling supports

Embodiments of the present airfoil systems comprise an airfoil with a leading edge, a trailing edge, an upper surface, a lower surface, and a skin surface, at least one structural element located within said airfoil, wherein said structural element supports the skin surface having an upper skin portion and a lower skin portion wherein said structural element can change its shape in response to external stimulus during flight operations, and an actuating means for selectively altering the curvature of said structural element which alters the curvature of said upper skin portion and of said lower skin portion to cause nonlinear deflection of said skin surface between an extreme raised position through a neutral position to an extreme lowered position; whereby the outer surface curvature of said airfoil and said skin surface is smooth and continuous over substantially the entirety thereof at all positions of said skin surface.

Embodiments of the present airfoil structural insert comprise an airfoil structural insert frame, a skin surface disposed about the airfoil structural insert frame, at least one attachment point operable for coupling to an aerodynamic structure, a leading edge disposed on one end of the airfoil structural insert frame, a trailing edge disposed on an opposite end of the airfoil structural insert frame, and at least one structural element configured to support the skin surface, wherein said structural element undergoes at least one nonlinear shape change from a first shape to a deflected shape.

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Miamisburg, OH, United States of America

Bryan Michael Pelley