Incorporation of Analysis Enhancements of a p-Element Analysis Code Required for Implementing the Strain Invariant Failure Theory

Award Information
Agency:
Department of Defense
Branch
Navy
Amount:
$1,499,310.00
Award Year:
2005
Program:
SBIR
Phase:
Phase II
Contract:
N68335-05-C-0021
Agency Tracking Number:
N032-0104
Solicitation Year:
2003
Solicitation Topic Code:
N03-169
Solicitation Number:
2003.2
Small Business Information
ENGINEERING SOFTWARE RESEARCH & DEVELOPM
10845 Olive Blvd., Suite 170, St. Louis, MO, 63141
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
859454886
Principal Investigator:
Randy Dennison
Sr. Project Engineer
(314) 983-0649
randy.dennison@esrd.com
Business Contact:
Barna Szabo
President / CEO
(314) 983-0649
barna.szabo@esrd.com
Research Institution:
n/a
Abstract
Historically, the correlation between predicted failure and actual failure of composite aircraft structures has left much to be desired. Current analytical prediction methods often over estimate or under estimate the failure load by 25% or more. Compounding the problem is that the failure of composite structure has led to a lengthy and costly, test-based certification process. A relatively new failure theory for composites, the Strain Invariant Failure Theory (SIFT), is proving to be far more accurate at predicting failure. SIFT in conjunction with a robust finite element analysis (FEA) tool offer an efficient method aimed at streamlining the design certification process for laminated composite structures. Phase 1 activities demonstrated proof of concept that the following features can be implemented into a p-element FEA code. - General Shell element with a transition to a 3D solid element - Laminated orthotropic material properties that follow a general curvature. - 2D & 3D Contact element and a 3D Fastener element. Phase 2 activities will fully develop these features and enable their use in a production environment.

* information listed above is at the time of submission.

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