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Prediction of Rotor Loads from Fuselage Sensors for Improved Structural Modeling and Fatigue Life Calculation

Award Information
Agency: Department of Defense
Branch: Navy
Contract: N68335-19-C-0192
Agency Tracking Number: N17A-009-0057
Amount: $999,844.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: N17A-T009
Solicitation Number: 17.A
Timeline
Solicitation Year: 2017
Award Year: 2019
Award Start Date (Proposal Award Date): 2019-03-20
Award End Date (Contract End Date): 2022-08-22
Small Business Information
3190 Fairview Park Drive Suite 650
Falls Church, VA 22042-0000
United States
DUNS: 010983174
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Chance Mccoll
 Director of Engineering - GA
 (770) 516-7750
 cmccoll@tda-i.com
Business Contact
 Patty Walk
Phone: (703) 226-4064
Email: pwalk@tda-i.com
Research Institution
 University of Maryland
 Danette Boon Danette Boon
 
Room 3112 Lee Building 7809 Regents Drive
College Park, MD 20742-0000
United States

 (301) 405-8108
 Nonprofit College or University
Abstract

Phase I addressed the technological gap in the predictive capabilities of CFD/FSI in the context of hybrid loads/sensor models used in an aircraft’s fatigue life tracking program for critical fuselage and dynamic components across the full flight regime. It demonstrated these technology advancements: (1) a combined rotor, fuselage aeroelastic model; (2) empirical rotor hub loads prediction from fuselage sensors; (3) innovative whole aircraft CFD/FSI/IMGA methods; (4) rotor hub loads to blade loads predictions; and (5) a strategy for required fuselage-based instrumentation. Phase II will improve the full aircraft structural dynamics model, including tail rotor, all dominant excitation modes, as well as component mode synthesis for enhanced modal super-elements for the fuselage and fatigue-critical main rotor hub component models, expand the aerodynamics model for full aircraft CFD/FSI/IMGA with performance optimized for use in a structural fatigue life tracking program, perform loads prediction validation for all flight regimes, and quantify this load prediction methodology via structural fatigue analysis for select rotor components. The fuselage sensors will be validated. These efforts will provide a solid platform for implementation in a US Navy structural fatigue life tracking program, and ultimately leading to enhanced safety and cost optimization due to improved, measurement-based rotorcraft loads prediction.

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

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