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The application of active controls technology to a generic hypersonic aircraft configurationAnalytical methods are described for the prediction of aerothermoelastic stability of hypersonic aircraft including active control systems. Thermal loads due to aerodynamic heating were applied to the finite element model of the aircraft structure and the thermal effects on flutter were determined. An iterative static aeroelastic trim analysis procedure was developed including thermal effects. And active control technology was assessed for flutter suppression, ride quality improvement, and gust load alleviation to overcome any potential adverse aeroelastic stability or response problems due to aerodynamic heating. A generic hypersonic aircraft configuration was selected which incorporates wing flaps, ailerons, and all moveable fins to be used for active control purposes. The active control system would use onboard sensors in a feedback loop through the aircraft flight control computers to move the surfaces for improved structural dynamic response as the aircraft encounters atmospheric turbulence.
Document ID
19900010755
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gilbert, M. G. (NASA Langley Research Center Hampton, VA., United States)
Heeg, J. (NASA Langley Research Center Hampton, VA., United States)
Pototzky, A. S. (Lockheed Engineering and Sciences Co. Hampton, VA., United States)
Spain, C. V. (Lockheed Engineering and Sciences Co. Hampton, VA., United States)
Soistmann, D. L. (Lockheed Engineering and Sciences Co. Hampton, VA., United States)
Dunn, H. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1990
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:101689
NASA-TM-101689
Meeting Information
Meeting: National Aero-Space Plane Technology Symposium
Location: Cleveland, OH
Country: United States
Start Date: October 1, 1989
Accession Number
90N20071
Funding Number(s)
PROJECT: RTOP 505-63-21-04
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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