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Adaptive flutter suppression, analysis and testMethods of adaptive control have been applied to suppress a potentially violent flutter condition of a half-span model of a lightweight figher aircraft. This marked the confluence of several technologies with active flutter suppression, digital control and adaptive control theory the primary contributors. The control algorithm was required to adapt both to slowly varying changes, corresponding to changes in the flight condition or fuel loading and to rapid changes, corresponding to a store release or the transition from a stable to an unstable flight condition. The development of the adaptive control methods was followed by a simulation and checkout of the complete system and a wind tunnel demonstration. As part of the test, a store was released from the model wing tip, transforming the model abruptly from a stable configuration to a violent flutter condition. The adaptive algorithm recognized the unstable nature of the resulting configuration and implemented a stabilizing control law in a fraction of a second. The algorithm was also shown to provide system stability over a range of wind tunnel Mach numbers and dynamic pressures.
Document ID
19830013948
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Johnson, E. H.
(Northrop Corp. Hampton, VA, United States)
Hwang, C.
(Northrop Corp.)
Joshi, D. S.
(Northrop Corp.)
Harvey, C. A.
(Honeywell, Inc.)
Huttsell, L. T.
(AFWAL)
Farmer, M. G.
(NASA Langley Research Center)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Publication Information
Publication: AGARD Recent Transonic Flutter Invest. for Wings and External Stores
Subject Category
Aircraft Stability And Control
Accession Number
83N22219
Distribution Limits
Public
Copyright
Other
Document Inquiry

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