The patent badge is an abbreviated version of the USPTO patent document. The patent badge does contain a link to the full patent document.

The patent badge is an abbreviated version of the USPTO patent document. The patent badge covers the following: Patent number, Date patent was issued, Date patent was filed, Title of the patent, Applicant, Inventor, Assignee, Attorney firm, Primary examiner, Assistant examiner, CPCs, and Abstract. The patent badge does contain a link to the full patent document (in Adobe Acrobat format, aka pdf). To download or print any patent click here.

Date of Patent:
Sep. 10, 2024

Filed:

Apr. 12, 2022
Applicant:

Cornerstone Research Group, Inc., Miamisburg, OH (US);

Inventors:

Ben Dietsch, Kettering, OH (US);

Bryan Pelley, Sugarcreek Township, OH (US);

Karl Gruenberg, Washington Township, OH (US);

Jason Hermiller, Lebanon, OH (US);

Assignee:

Cornerstone Research Group, Inc., Miamisburg, OH (US);

Attorney:
Primary Examiner:
Int. Cl.
CPC ...
B29B 11/12 (2006.01); B29B 11/16 (2006.01); B29C 65/48 (2006.01); B29C 65/56 (2006.01); B29C 70/12 (2006.01); B29C 70/34 (2006.01); B64F 5/10 (2017.01); B29K 105/12 (2006.01); B29K 307/04 (2006.01); B29L 31/30 (2006.01);
U.S. Cl.
CPC ...
B64F 5/10 (2017.01); B29B 11/12 (2013.01); B29B 11/16 (2013.01); B29C 65/4835 (2013.01); B29C 65/565 (2013.01); B29C 70/12 (2013.01); B29C 70/34 (2013.01); B29K 2105/12 (2013.01); B29K 2307/04 (2013.01); B29L 2031/3076 (2013.01);
Abstract

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.


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