The Boeing Company

Rudy Braun

Marc Storozuk

Geoffrey Gibbings

Bruce Taylor

Kyle Christopher Advent

Gagan Thable

Michael A Baschak

A composite component assembly may include a composite core including a plurality of core cells between first and second ends. A connection joint is formed between the first and second ends. An adhesive layer is disposed within the connection joint between the first and second ends. The adhesive layer is configured to bond the first and second ends through a curing process. A peg splice securing joint securely connects the first and second ends together before and during the curing process.

System and method for securely connecting portions of a composite structure together

In an embodiment of the disclosure, there is provided a panel assembly for joining to a structure and method of making the same. The assembly has a first panel element having at least one first panel nonlinear edge, and has a second panel element having at least one second panel nonlinear edge, wherein the second panel nonlinear edge is designed to interlace with the first panel nonlinear edge to form a panel assembly with interlaced panel edgebands for joining to a structure. A width of the interlaced panel edgebands is reduced as compared to a width of adjacent panel edgebands formed by adjacent panel elements having linear edges, and the reduced width results in an overall reduced weight of the panel assembly and the structure to which the panel assembly is joined.

Panel assembly and method of making the same

Growing community of inventors

Winnipeg, Canada

Rudy Braun