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Proceedings Paper

Design, fabrication, and testing of scaled wind tunnel model for the Smart Wing Phase 2 program
Author(s): Christopher A. Martin; Brian J. Hallam; John S. Flanagan; Jonathan D. Bartley-Cho
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Paper Abstract

Building on the research performed during the DARPA/AFRL Smart Wing Phase 1 program to improve vehicle aerodynamic efficiency using control surfaces actuated by smart materials, the goal of the Phase 2 effort was to increase the size of the model and its control surfaces while also increasing the test dynamic pressure, Mach number and control surface deflection rate. To test the high rate, hingeless smart actuators a 30 percent scale wind tunnel model of a proposed Northrop Grumman Corporation uninhabited combat air vehicle was designed and tested. This paper describes the design, fabrication, system integration, and ground test results of the Smart Wing Phase 2 model. Among the topics that will be covered are (1) wind tunnel model selection; (2) analysis and design procedure; (3) smart control surface integration; and (4) static load and ground vibration test results and correlation.

Paper Details

Date Published: 9 July 2002
PDF: 9 pages
Proc. SPIE 4698, Smart Structures and Materials 2002: Industrial and Commercial Applications of Smart Structures Technologies, (9 July 2002); doi: 10.1117/12.475091
Show Author Affiliations
Christopher A. Martin, Northrop Grumman Corp. (United States)
Brian J. Hallam, Northrop Grumman Corp. (United States)
John S. Flanagan, Northrop Grumman Corp. (United States)
Jonathan D. Bartley-Cho, Northrop Grumman Corp. (United States)


Published in SPIE Proceedings Vol. 4698:
Smart Structures and Materials 2002: Industrial and Commercial Applications of Smart Structures Technologies
Anna-Maria Rivas McGowan, Editor(s)

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