Wind tunnel testing of a variable camber compliant wing with a unique dual load cell test fixture

Date of Award

2015

Degree Name

M.S. in Aerospace Engineering

Department

Department of Mechanical and Aerospace Engineering

Advisor/Chair

Advisor: Aaron Altman

Abstract

This thesis describes the design, setup, and testing of a unique mounting fixture built for the Variable Camber Compliant Wing developed by the U.S. Air Force Research Laboratory. The intent of the Variable Camber Compliant Wing is to demonstrate an active 2D section camber change under aerodynamic load. Mounting possibilities were limited in the Vertical Wind Tunnel due to the dimensions and weight of the wing which necessitated a custom design to obtain aerodynamic force measurements. ATI Industrial Automation offers a promising solution with their wide range of multi-axis force/torque sensors which are becoming widely adopted in aerodynamic testing of small unmanned aircraft. These sensors can provide accurate results when loaded in close proximity to the balance center. However, it has been reported in literature that measurement error increases dramatically when the balance is loaded off balance center. In this case, a load cell is mounted on each end of the unique fixture, forming a direct interaction between the two load cells. An extensive calibration loading procedure was performed prior to the test to develop a calibration matrix sensitive to the test setup. The intent of this thesis is to present development of a correction method for this unique mounting fixture which could provide a new flexible wing testing capability in the Vertical Wind Tunnel Facility at the Air Force Research Laboratory.

Keywords

Detectors Calibration, Airplanes Parts Design and construction, Airplanes Wings Testing, Aerospace Engineering, Engineering, Variable Camber Compliant Wing, Dual Load Cell, Test Fixture Validation, Calibration Loading

Rights Statement

Copyright © 2015, author

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