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Virtual Deformation Control of the X-56A Model with Simulated Fiber Optic SensorsA 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-of-attack 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.
Document ID
20140008927
Acquisition Source
Armstrong Flight Research Center
Document Type
Conference Paper
Authors
Suh, Peter M. (NASA Dryden Flight Research Center Edwards, CA United States)
Chin, Alexander Wong (NASA Dryden Flight Research Center Edwards, CA United States)
Date Acquired
July 9, 2014
Publication Date
August 19, 2013
Subject Category
Aircraft Stability And Control
Report/Patent Number
DFRC-E-DAA-TN10283
Meeting Information
Meeting: AIAA Atmospheric Flight Mechanics Conference
Location: Boston, MA
Country: United States
Start Date: August 19, 2013
End Date: August 22, 2013
Sponsors: American Inst. of Aeronautics and Astronautics
Distribution Limits
Public
Copyright
Public Use Permitted.
Keywords
Modal Filter
Distributed Sensing
Controls

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