Back to results
US 4,715,560 AGranted
Composite cruciform structure for joining intersecting structural members of an airframe and the like
AssigneeLear Fan Corp.
InventorErnie F. Loyek
Life of this patent
Estimating the term…
Loading patent…
Loading patent…
AssigneeLear Fan Corp.
InventorErnie F. Loyek
Estimating the term…
A composite cruciform structure adapted for securely joining two or more intersecting fiber based composite structural members of an airframe and the like, is disclosed. A first bundle of graphite or other fibers of high strength is intimately interwoven with a second bundle of like fibers, with each bundle of fibers extending in a different direction and being aligned with the general longitudinal axis of a respective first and second composite structural member. A third bundle of fibers is interwoven with both the first and second bundles of fibers to form the cruciform structure. The bundles of fibers are reinforced with a suitable cured resin. The cruciform structure may comprise an integral part of the respective structural members, or may be attached thereto by splicing. The cruciform allows for substantially even distribution of structural loads regardless of the direction of the corresponding load force vectors, and is most advantageously utilized in the construction of high strength and low weight airframes.
An aircraft structure comprising non-intersecting structural elements and intersecting structural elements, the intersecting structural elements being of a composite cruciform structure having intersecting structural members, and the non-intersecting structural elements being elongated planar elements extending between and overlapping adjacent structural members of adjacent intersecting structural elements of the cruciform structure, said cruciform structure comprising a first bundle of fibers interwoven with a second bundle of fibers and additional fibers interwoven with each of said first and second bundles of fibers in a direction substantially perpendicular to the fibers of said first and second bundles, to form said cruciform structure, said fibers having a reinforcing resin on the surface thereof to provide a strong substantially rigid structure joinder of said structural members without a substantia1 break in the continuity of the fibers and to provide substantially even load bearing and force transmitting capability in a plurality of directions with respect to said intersection of sid structural members.
An aircraft structure comprising non-intersecting structural elements and intersecting structural elements, the intersecting structural elements being of a composite cruciform structure having intersectng structural members, the non-intersecting structural elements being elongated planar elements extending between and overlapping adjacent structural members of adjacent intersecting structural elements of the cruciform structure, said cruciform structure comprising a first bundle of fibers interwoven with a second bundle of fibers, and additional bundles of fibers disposed substantially perpendicular to said first and second bundles of fibers and interwoven with both said first and second bundles to form said cruciform structure, said fibers being selected from the group consisting of carbon, graphite, Kevlar, glass and boron fibers, each of said bundles of fibers comprising a plurality of layers of fibers, said bundles being provided with a reinforcing resin on the surface thereof, to provide a strong substantially rigid structural joinder of said structural members without a substantial break in the continuity of said fibers and to provide substantial even load bearing and force transmitting capability in a plurality of directions with respect to said intersecting of said structural members.
A process for forming structures comprising non-intersecting structural elements and intersecting structural elements by strongly and substantially rigidly joining first substantially elongated composite structural members and second substantially elongated composite structural members which form the intersecting structural elements, said first and second structural members extending in different directions relative to one another, the process comprising the steps of:
Dependencies are inferred from the claim text.