Combined Analytical and Experimental Approaches to Rotor and Dynamic Component Stress Predictions

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-08-C-0158
Agency Tracking Number: N081-021-1368
Amount: $79,999.00
Phase: Phase I
Program: SBIR
Awards Year: 2008
Solicitation Year: 2008
Solicitation Topic Code: N08-021
Solicitation Number: 2008.1
Small Business Information
2845 E. 2nd Street, Tucson, AZ, 85716
DUNS: 627888675
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Ali Boufelfel
 Senior Scientist
 (520) 250-1399
Business Contact
 Erdogan Madenci
Title: President
Phone: (520) 250-1399
Research Institution
Recent studies have made an attempt to couple computational structural dynamic tools with sophisticated computational fluid dynamic (CFD) solvers. The CFD approach is still at a nascent stage and discrepancies can be observed in both phase and amplitude of the predicted load. Due to the inefficiencies of the currently available aerodynamic models, load predictions will have to rely on experimentally measured aerodynamic loads. Therefore, a coupled approach involving both an analytical methodology for structural analysis and experimentally measured aerodynamic loads should be employed to predict individual component loads as well as the stress and strain field in critical locations. These results can then be utilized for damage tolerance and failure prediction of the individual components. The structural model should not only be able to capture the dynamic load experienced by components such as the pitch link, swashplate, hub or trailing edge flap but also detailed stress and strain field in each ply of the composite blade. Therefore, a validated three- dimensional analysis capability is required for structural dynamic analysis of rotor blades to make accurate load and stress predictions. For this purpose, Global Engineering and Research Technologies will improve and validate an existing in-house code.

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

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