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Full-Field Reconstruction of Structural Deformations and Loads from Measured Strain Data on a Wing Using the Inverse Finite Element MethodA study was undertaken to investigate the measurement of wing deformation and internal loads using measured strain data. Future aerospace vehicle research depends on the ability to accurately measure the deformation and internal loads during ground testing and in flight. The approach uses the inverse Finite Element Method (iFEM). The iFEM is a robust, computationally efficient method that is well suited for real-time measurement of real-time structural deformation and loads. The method has been validated in previous work, but has yet to be applied to a large-scale test article. This work is in preparation for an upcoming loads test of a half-span test wing in the Flight Loads Laboratory at the National Aeronautics and Space Administration Armstrong Flight Research Center (Edwards, California). The method has been implemented into an efficient MATLAB® (The MathWorks, Inc., Natick, Massachusetts) code for testing different sensor configurations. This report discusses formulation and implementation along with the preliminary results from a representative aerospace structure. The end goal is to investigate the modeling and sensor placement approach so that the best practices can be applied to future aerospace projects.
Document ID
20160014695
Acquisition Source
Armstrong Flight Research Center
Document Type
Technical Memorandum (TM)
Authors
Miller, Eric J. (NASA Armstrong Flight Research Center Edwards, CA United States)
Manalo, Russel (Intern, Dryden Edwards, CA, United States)
Tessler, Alexander (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
December 19, 2016
Publication Date
November 1, 2016
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2016-219407
DFRC-E-DAA-TN36196
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Finite element
structures
deformation equations

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