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Design, implementation and experimental testing of an inertial sensor system to quantify wing deflection
Schirmer, Georg
Schirmer, Georg
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Dissertation
Adobe PDF, 59.48 MB
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2019-05
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Dissertation
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Electronic dissertations
Electronic dissertations
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Abstract
This research investigates a novel approach of using inertial micro-electromechanical
sensors in combination with a Kalman state estimator to quantify wing deflection of a highly
flexible morphing wing. Motivated by NASA's and Boeing?s collaborative research into multiobjective
control of a highly flexible morphing wing, the work described herein illustrates the
development and implementation of wing shape output feedback part of such a system. Equations
for prediction and measurement are developed to estimate bending and torsion. Initially a static
structural model serves as a means to construct deflection measurements using sensor data.
System inputs are obtained using 3-axis accelerometers and gyroscopes. Sensor fusion of
accelerometer and gyroscopic data is discussed. The system is expanded to incorporate a
structural dynamics finite element model for the prediction and advanced inertial measurement
unit motion processors to take measurements. Sensor analysis is performed to determine sensor
specific performance characteristics which are used for the state estimator design. Extensive
bench and wind tunnel testing of the final system design was conducted. The implementation,
static and dynamic deflection testing and results of the system design are discussed. Future work
is proposed and includes the development of a more advanced structural FEM model and the use
of higher accuracy sensors units.
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Thesis (Ph.D.)-- Wichita State University, College of Engineering, Dept. of Aerospace Engineering
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Wichita State University
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Copyright 2019 by Georg Schirmer
All Rights Reserved