Design, fabrication, and testing of scaled wind tunnel model for the Smart Wing Phase 2 program

Christopher A. Martin; Brian J. Hallam; John S. Flanagan; Jonathan D. Bartley-Cho

doi:10.1117/12.475091

9 July 2002 Design, fabrication, and testing of scaled wind tunnel model for the Smart Wing Phase 2 program

Christopher A. Martin, Brian J. Hallam, John S. Flanagan, Jonathan D. Bartley-Cho

Proceedings Volume 4698, Smart Structures and Materials 2002: Industrial and Commercial Applications of Smart Structures Technologies; (2002) https://doi.org/10.1117/12.475091
Event: SPIE's 9th Annual International Symposium on Smart Structures and Materials, 2002, San Diego, California, United States

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.

Citation Download Citation

Christopher A. Martin, Brian J. Hallam, John S. Flanagan, and Jonathan D. Bartley-Cho "Design, fabrication, and testing of scaled wind tunnel model for the Smart Wing Phase 2 program", Proc. SPIE 4698, Smart Structures and Materials 2002: Industrial and Commercial Applications of Smart Structures Technologies, (9 July 2002); https://doi.org/10.1117/12.475091

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