Innovative Method for Real-Time Damage Alleviation

Award Information
Agency:
Department of Defense
Branch:
Navy
Amount:
$749,976.00
Award Year:
2013
Program:
SBIR
Phase:
Phase II
Contract:
N68335-13-C-0124
Agency Tracking Number:
N112-118-0034
Solicitation Year:
2011
Solicitation Topic Code:
N112-118
Solicitation Number:
2011.2
Small Business Information
Technical Data Analysis, Inc.
3190 Fairview Park Drive, Suite 650, Falls Church, VA, -
Hubzone Owned:
N
Socially and Economically Disadvantaged:
N
Woman Owned:
N
Duns:
010983174
Principal Investigator
 Chance McColl
 Director of Engineering -
 (770) 516-7750
 cmccoll@tda-i.com
Business Contact
 Scott Bradfield
Title: President
Phone: (703) 226-4061
Email: sbradfield@tda-i.com
Research Institution
N/A
Abstract
Deployment of Health and Usage Monitoring Systems (HUMS) on rotorcraft has resulted in significant improvements in maintenance action efficiency, increases in safety, and reductions in cost. Current HUMS provide diagnostic and prognostic information to maintenance crews through Condition Based Maintenance (CBM), which allows parts to be replaced on an as-needed basis. This marks an improvement over legacy approaches, which relied on conservative life estimates that resulted in early component retirement due to a lack of accurate component usage data to determine actual component life. HUMS has shown its value over time, yet it is still a passive system that provides no active fatigue damage alleviation. This SBIR effort is focused on the development of a HUMS interface which will automatically reduce the damage on aircraft components in real-time by modifying the control system output, allowing component life to be extended beyond that which has been realized with HUMS alone. In addition, through control system output modification, damage rates on specific components may be tailored to extend the life up to the next scheduled maintenance activity. The development of a system to track the amount of damage occurring on this component allows for optimization of the flight control system output to reduce structural component damage while maintaining the required maneuverability, flying quality, and handling qualities.

* information listed above is at the time of submission.

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