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Accession Number N14-0003967
Title Virtual Deformation Control of the X-56A Model with Simulated Fiber Optic Sensors.
Publication Date Jan 2014
Media Count 39p
Personal Author A. W. Chin D. N. Mavris P. M. Suh
Abstract A robust control law design methodology is presented to stabilize the X-56A model and command its wing shape. The X-56A was purposely designed to experience flutter modes in its flight envelope. The methodology introduces three phases: the controller design phase, the modal filter design phase, and the reference signal design phase. A mu-optimal controller is designed and made robust to speed and parameter variations. A conversion technique is presented for generating sensor strain modes from sensor deformation mode shapes. The sensor modes are utilized for modal filtering and simulating fiber optic sensors for feedback to the controller. To generate appropriate virtual deformation reference signals, rigid-body corrections are introduced to the deformation mode shapes. After successful completion of the phases, virtual deformation control is demonstrated. The wing is deformed and it is shown that angle-ofattack changes occur which could potentially be used to an advantage. The X-56A program must demonstrate active flutter suppression. It is shown that the virtual deformation controller can achieve active flutter suppression on the X-56A simulation model.
Keywords Aerodynamic stability
Control systems design
Control theory
Feedback control
Fiber optics
Flexible wings
Least squares method
Mathematical models
Shape control
Vibration damping

Source Agency National Aeronautics and Space Administration
NTIS Subject Category 51C - Aircraft
51B - Aeronautics
Corporate Author National Aeronautics and Space Administration, Edwards, CA. Hugh L. Dryden Flight Research Center.
Document Type Technical report
Title Note N/A
NTIS Issue Number 1421
Contract Number N/A

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