CORE STRUCTURES FOR COMPOSITE PANELS, AIRCRAFT INCLUDING THE SAME, AND RELATED METHODS

Core structures for composite panels, aircraft including the same, and related methods. A core structure includes a core body defining a first body side, a second body side, and a plurality of core cells. Each core cell includes at least one cell wall and defines a tubular cell void. Each core cell...

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Bibliographische Detailangaben
1. Verfasser:	SERENCSITS, William L
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING LAYERED PRODUCTS LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT ORNON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM PERFORMING OPERATIONS SHAPING CLAY OR OTHER CERAMIC COMPOSITIONS, SLAG, OR MIXTURESCONTAINING CEMENTITIOUS MATERIAL, e.g. PLASTER SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR SHAPING OR JOINING OF PLASTICS TRANSPORTING WORKING CEMENT, CLAY, OR STONE WORKING OF PLASTICS WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL
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Beschreibung
Zusammenfassung:	Core structures for composite panels, aircraft including the same, and related methods. A core structure includes a core body defining a first body side, a second body side, and a plurality of core cells. Each core cell includes at least one cell wall and defines a tubular cell void. Each core cell includes a bulk region and a transition region. Each cell wall is flared within the transition region to increase a surface area of the first body side relative to an average transverse cross-sectional area of the core body. A composite panel includes a core structure with at least one laminate ply coupled to the first body side of a core body. A method of manufacturing a composite panel includes forming a core body via an additive manufacturing process and operatively attaching at least one laminate ply to the core body.