Innovative Analysis Tool for Damage Growth From Loaded Composite Fastener Holes

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$79,938.00
Award Year:
2009
Program:
SBIR
Phase:
Phase I
Contract:
N68335-09-C-0454
Award Id:
92610
Agency Tracking Number:
N092-095-0644
Solicitation Year:
n/a
Solicitation Topic Code:
n/a
Solicitation Number:
n/a
Small Business Information
GLOBAL ENGINEERING & MATERIALS, INC. (Currently Global Engineering and Materials, Inc)
11 Alscot Drive, East Lyme, CT, 06333
Hubzone Owned:
N
Minority Owned:
N
Woman Owned:
N
Duns:
610056405
Principal Investigator:
Jim Lua
President
(860) 367-4970
jlua@gem-consultant.com
Business Contact:
Jim Lua
President
(860) 367-4970
jlua@gem-consultant.com
Research Institution:
n/a
Abstract
A software tool for residual strength and life prediction of composite bolted joints will be developed by enhancing and integrating an existing mesh independent delamination and matrix cracking network model in ABAQUS. The tool will be able to model arbitrary location, size of damage, and geometric configuration of a composite structure with fastener holes without user intervention or remeshing. High computational efficiency and modeling fidelity is achieved via the integration of the discrete crack network model with a hybrid fatigue damage model within ABAQUS' computational framework. Global Engineering and Materials, Inc. (GEM) has secured commitments for technical support from UDRI, LM Aero, and SIMULIA, who will provide existing solution modules, supporting data, customization plug-ins, and expertise. In addition, Dr. Iarve from UDRI will provide GEM with his stand alone 3D bolted joint stress analysis and damage growth prediction tool that has been in development for more than 10 years under the sponsorship of Air Force and NASA. The multi-faceted feasibility study consists of developing a method that will enable the prediction of multi-site, multi-mode damage initiation, propagation, and interaction in composite bolted joints subjected to monotonic and fatigue loading.

* information listed above is at the time of submission.

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