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Analysis Tool to Predict the Behavior of Bolted Composite/Metallic Hybrid Joints with Many Fasteners

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-19-P-2039
Agency Tracking Number: F182-062-1371
Amount: $149,998.00
Phase: Phase I
Program: SBIR
Solicitation Topic Code: AF182-062
Solicitation Number: 2018.2
Solicitation Year: 2018
Award Year: 2019
Award Start Date (Proposal Award Date): 2019-02-28
Award End Date (Contract End Date): 2020-02-28
Small Business Information
1200 N Eldorado Pl, Tucson, AZ, 85715
DUNS: 627888675
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Ali Boufelfel
 (520) 499-2791
Business Contact
 Ibrahim Guven
Phone: (520) 499-2791
Research Institution
Increased use of composites in USAF platforms, and in commercial aircraft necessitates accurate structural analysis of bolted joints.The main disadvantage of bolted joints is the formation of high stress concentration zones at the locations of bolt holes, which might lead to multi-mode failure of the joint.An optimum combination of geometric parameters in a bolted joint can lead to increases in joint strength. However, there is no analysis capability that can predict all possible failure modes concerning bolted joints.The analysis method should provide the deformation of each laminate, non-linear bearing deformation, complete stress and strain fields while accounting for material stiffness degradation, through the thickness stress variation, and state of progressive failure.The goal of this proposed project is to develop an analysis tool by combining the method developed by GERT and the peridynamic theory for achieving structurally efficient bolted lap joints with optimum combination of material and geometric parameters.This tool will enable the designers to consider complex lap joint designs of multiple dissimilar composite and metal layers with staggered bolts while accounting for the contact phenomenon, the presence of friction, the interaction among the bolts under complex bearing and by-pass loading for progressive failure analysis.

* Information listed above is at the time of submission. *

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