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Embedded Structural Integrity Sensor

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: NNL07AA98P
Agency Tracking Number: 060416
Amount: $99,980.00
Phase: Phase I
Program: STTR
Solicitation Topic Code: T7.01
Solicitation Number: N/A
Timeline
Solicitation Year: 2006
Award Year: 2007
Award Start Date (Proposal Award Date): 2007-01-19
Award End Date (Contract End Date): 2008-01-18
Small Business Information
2851 Commerce Street
Blacksburg, VA 24060-6657
United States
DUNS: 627132913
HUBZone Owned: Yes
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Mark McKenna
 Principal Investigator
 (540) 552-5128
 submissions@lunainnovations.com
Business Contact
 Angela Keen
Title: Business Official
Phone: (540) 552-5128
Email: submissions@lunainnovations.com
Research Institution
 Pennsylvania State University
 Not Available
 
110 Technology Center, 200 Innovation Blvd.
University Park, PA 16802
United States

 (814) 865-1372
 Domestic Nonprofit Research Organization
Abstract

In this work Luna Innovations in partnership with Pennsylvania State University proposes to develop a new thermo-ultrasonic technology for the real-time in-situ monitoring of critical metallic, composite and bonded structural health parameters during space exploration missions. The potential applications of the proposed technique include characterization of component response to loading, monitoring load distribution, and identifying stresses exceeding design in a variety of structural materials and geometries. Another important usage area is assessment of the effects of structural defects on the system's performance, early detection of damage, and prediction of the remaining service life of critical components. The technology will utilize sparse networks of built-in or surface-mounted miniature lightweight ultrasonic sensors with low power consumption levels suitable for space deployment. A combination of specially designed sensor excitation mechanism and accurate velocimetry yields very high sensitivity to critical structural performance parameters. In Phase I we will demonstrate feasibility of the proposed approach on laboratory specimens subjected to load, and verify the results against mathematical models and FEM simulation. In Phase II we will develop a full-featured prototype unit and demonstrate all the benefits of the new technology on a representative flight component.

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

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