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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.

Patent No.:

US 8916252 B1

PDFFull Text
Date of Patent:
Dec. 23, 2014

Filed:

Jun. 11, 2009

Structural longitudinal composite joint for aircraft structure

Applicants:

Per Hallander, Linköping, SE;

Mikael Petersson, Linköping, SE;

Bjorn Weidmann, Borensberg, SE;

Tommy Grankäll, Borensberg, SE;

Göte Strindberg, Linköping, SE;

Pontus Nordin, Linköping, SE;

Rustan Önnefors, Linköping, SE;

Inventors:

Per Hallander, Linköping, SE;

Mikael Petersson, Linköping, SE;

Bjorn Weidmann, Borensberg, SE;

Tommy Grankäll, Borensberg, SE;

Göte Strindberg, Linköping, SE;

Pontus Nordin, Linköping, SE;

Rustan Önnefors, Linköping, SE;

Assignee:

SAAB AB, Linköping, SE;

Attorneys:

Venable LLP

Eric J. Franklin

Primary Examiner:

Brent O'Hern

Int. Cl.
CPC ...
B32B 3/14 (2006.01); B32B 7/14 (2006.01); B29C 70/58 (2006.01); B29C 65/50 (2006.01); B29C 65/00 (2006.01); B29C 70/30 (2006.01); B32B 3/02 (2006.01); B32B 5/26 (2006.01); B32B 5/28 (2006.01); B64C 3/20 (2006.01); B64C 3/26 (2006.01); B29C 65/48 (2006.01); B29K 31/00 (2006.01); B29K 63/00 (2006.01); B29K 67/00 (2006.01); B29K 71/00 (2006.01); B29K 79/00 (2006.01); B29K 81/00 (2006.01); B29K 101/10 (2006.01); B29K 101/12 (2006.01); B29K 105/06 (2006.01); B29K 105/16 (2006.01); B29K 307/00 (2006.01); B29K 309/02 (2006.01); B29K 309/08 (2006.01); B29L 31/30 (2006.01);
U.S. Cl.
CPC ...
B29C 70/58 (2013.01); B29C 65/5057 (2013.01); B29C 66/1142 (2013.01); B29C 66/43 (2013.01); B29C 66/721 (2013.01); B29C 70/30 (2013.01); B32B 3/02 (2013.01); B32B 5/26 (2013.01); B32B 5/28 (2013.01); B64C 3/20 (2013.01); B64C 3/26 (2013.01); B29C 65/5014 (2013.01); B29C 65/5021 (2013.01); B29C 65/4875 (2013.01); B29C 65/488 (2013.01); B29C 66/435 (2013.01); B29K 2031/00 (2013.01); B29K 2063/00 (2013.01); B29K 2067/00 (2013.01); B29K 2071/00 (2013.01); B29K 2079/085 (2013.01); B29K 2081/04 (2013.01); B29K 2101/10 (2013.01); B29K 2101/12 (2013.01); B29K 2105/06 (2013.01); B29K 2105/167 (2013.01); B29K 2307/00 (2013.01); B29K 2309/02 (2013.01); B29K 2309/08 (2013.01); B29L 2031/3076 (2013.01); B29L 2031/3085 (2013.01); Y02T 50/433 (2013.01); Y02T 50/43 (2013.01);
Abstract

A structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure arranged within the composite joint. A method of producing a structural composite part made of pre-impregnated fiber plies. The edges of two adjacent fiber plies are connected via a longitudinal composite joint made structural by a nanostructure and an aircraft structure comprising such structural composite parts.

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