Show simple item record

dc.contributor.authorSchirmer, Georg
dc.contributor.authorSteck, James E.
dc.contributor.authorChakravarthy, Animesh
dc.date.accessioned2019-07-31T14:13:49Z
dc.date.available2019-07-31T14:13:49Z
dc.date.issued2019-01-06
dc.identifier.citationSchirmer, Georg; Steck, James E.; Chakravarthy, Animesh. 2019. Design, implementation and experimental testing of an inertial sensor system to quantify wing deflection.en_US
dc.identifier.isbn978-162410578-4
dc.identifier.urihttps://doi.org/10.2514/6.2019-1539
dc.identifier.urihttp://hdl.handle.net/10057/16498
dc.descriptionClick on the DOI link to access the article (may not be free).en_US
dc.description.abstractThis 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.en_US
dc.language.isoen_USen_US
dc.publisherAmerican Institute of Aeronautics and Astronautics Inc.en_US
dc.relation.ispartofseriesAIAA Scitech Forum: Session Fusion II;2019
dc.subjectAccelerometersen_US
dc.subjectAviationen_US
dc.subjectDeflection (structures)en_US
dc.subjectFlexible wingsen_US
dc.subjectNASAen_US
dc.subjectState estimationen_US
dc.subjectStructural dynamicsen_US
dc.subjectWind tunnelsen_US
dc.titleDesign, implementation and experimental testing of an inertial sensor system to quantify wing deflectionen_US
dc.typeConference paperen_US
dc.rights.holder© 2019 American Institute of Aeronautics and Astronauticsen_US


Files in this item

FilesSizeFormatView

There are no files associated with this item.

This item appears in the following Collection(s)

  • AE Research Publications [111]
    Research publications authored by the Department of Aerospace Engineering faculty and graduate students.

Show simple item record