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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 11491766 B1

PDFFull Text
Date of Patent:
Nov. 08, 2022

Filed:

Aug. 29, 2016

Hybrid metal composite structures, rocket motors and multi stage rocket motor assemblies including hybrid metal composite structures, and related methods

Applicant:

Northrop Grumman Systems Corporation, Falls Church, VA (US);

Inventors:

Benjamin W. C. Garcia, Tremonton, UT (US);

Braden Day, Nibley, UT (US);

Brian Christensen, Willard, UT (US);

David R. Nelson, Logan, UT (US);

Thomas Loveless, Logan, UT (US);

Elizabeth Bonderson, Pleasant View, UT (US);

Assignee:

Northrop Grumman Systems Corporation, Falls Church, VA (US);

Attorney:

TraskBritt

Primary Examiner:

Todd E Manahan

Assistant Examiner:

Kyle Robert Thomas

Int. Cl.
CPC ...
B32B 15/14 (2006.01); B32B 3/26 (2006.01); F02K 9/97 (2006.01); F02K 9/76 (2006.01); B32B 7/04 (2019.01); B32B 9/04 (2006.01); B32B 15/09 (2006.01); B32B 15/08 (2006.01); B32B 5/30 (2006.01); B32B 15/088 (2006.01); B32B 15/085 (2006.01); B32B 7/02 (2019.01); B32B 9/00 (2006.01); B32B 15/082 (2006.01); B32B 5/06 (2006.01); B32B 27/28 (2006.01); B32B 27/42 (2006.01); B32B 27/36 (2006.01); B32B 27/06 (2006.01); B32B 5/02 (2006.01); B32B 5/16 (2006.01); B32B 5/22 (2006.01); B32B 27/34 (2006.01); B32B 15/18 (2006.01); B32B 15/092 (2006.01); B32B 27/30 (2006.01); B32B 15/20 (2006.01); B32B 15/098 (2006.01); B32B 15/095 (2006.01); B32B 27/32 (2006.01); B32B 27/38 (2006.01); F02K 9/60 (2006.01); B32B 3/08 (2006.01); B32B 27/40 (2006.01);
U.S. Cl.
CPC ...
B32B 15/14 (2013.01); B32B 3/08 (2013.01); B32B 3/266 (2013.01); B32B 5/024 (2013.01); B32B 5/06 (2013.01); B32B 5/16 (2013.01); B32B 5/22 (2013.01); B32B 5/30 (2013.01); B32B 7/02 (2013.01); B32B 7/04 (2013.01); B32B 9/005 (2013.01); B32B 9/007 (2013.01); B32B 9/04 (2013.01); B32B 9/041 (2013.01); B32B 15/08 (2013.01); B32B 15/082 (2013.01); B32B 15/085 (2013.01); B32B 15/088 (2013.01); B32B 15/09 (2013.01); B32B 15/092 (2013.01); B32B 15/095 (2013.01); B32B 15/098 (2013.01); B32B 15/18 (2013.01); B32B 15/20 (2013.01); B32B 27/06 (2013.01); B32B 27/281 (2013.01); B32B 27/285 (2013.01); B32B 27/286 (2013.01); B32B 27/288 (2013.01); B32B 27/302 (2013.01); B32B 27/304 (2013.01); B32B 27/32 (2013.01); B32B 27/34 (2013.01); B32B 27/36 (2013.01); B32B 27/365 (2013.01); B32B 27/38 (2013.01); B32B 27/40 (2013.01); B32B 27/42 (2013.01); F02K 9/60 (2013.01); F02K 9/76 (2013.01); F02K 9/97 (2013.01); B32B 2250/42 (2013.01); B32B 2260/021 (2013.01); B32B 2260/025 (2013.01); B32B 2260/046 (2013.01); B32B 2262/02 (2013.01); B32B 2262/023 (2013.01); B32B 2262/0238 (2013.01); B32B 2262/0253 (2013.01); B32B 2262/0269 (2013.01); B32B 2262/0276 (2013.01); B32B 2262/0292 (2013.01); B32B 2262/101 (2013.01); B32B 2262/103 (2013.01); B32B 2262/105 (2013.01); B32B 2262/106 (2013.01); B32B 2307/30 (2013.01); B32B 2307/306 (2013.01); B32B 2307/51 (2013.01); B32B 2307/536 (2013.01); B32B 2307/546 (2013.01); B32B 2307/554 (2013.01); B32B 2307/7145 (2013.01); B32B 2307/72 (2013.01); B32B 2307/7248 (2013.01); B32B 2307/732 (2013.01); B32B 2605/00 (2013.01); F05D 2300/10 (2013.01); F05D 2300/603 (2013.01);
Abstract

A hybrid metal composite (HMC) structure comprises tiers comprising fiber composite material structures, and additional tiers longitudinally adjacent one or more of the tiers and comprising perforated metallic structures and additional fiber composite material structures laterally adjacent the perforated metallic structures. Methods of forming an HMC structure, and related rocket motors and multi-stage rocket motor assemblies are also disclosed.

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