Design, implementation and experimental testing of an inertial sensor system to quantify wing deflection
Schirmer, Georg Steck, James E. Chakravarthy, Animesh
Schirmer, Georg
Steck, James E.
Chakravarthy, Animesh
Authors
Schirmer, Georg
Steck, James E.
Chakravarthy, Animesh
Steck, James E.
Chakravarthy, Animesh
Other Names
Location
Time Period
Advisors
Original Date
Digitization Date
Issue Date
2019-01-06
Type
Conference paper
Genre
Keywords
Accelerometers,Aviation,Deflection (structures),Flexible wings,NASA,State estimation,Structural dynamics,Wind tunnels
Subjects (LCSH)
Citation
Schirmer, Georg; Steck, James E.; Chakravarthy, Animesh. 2019. Design, implementation and experimental testing of an inertial sensor system to quantify wing deflection.
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 multi-objective 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. This paper presents the implementation, static and dynamic deflection testing and results of the system design. Remaining work is proposed and includes experimental wind tunnel evaluation of the dynamic structural FEM model followed by a thorough error analysis.
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Publisher
American Institute of Aeronautics and Astronautics Inc.
Journal
Book Title
Series
AIAA Scitech Forum: Session Fusion II;2019