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Active control of aerothermoelastic effects for a conceptual hypersonic aircraftProcedures for and results of aeroservothermoelastic studies are described. The objectives of these studies were to develop the necessary procedures for performing an aeroelastic analysis of an aerodynamically heated vehicle and to analyze a configuration in the classical cold state and in a hot state. Major tasks include the development of the structural and aerodynamic models, open loop analyses, design of active control laws for improving dynamic responses and analyses of the closed loop vehicles. The analyses performed focused on flutter speed calculations, short period eigenvalue trends and statistical analyses of the vehicle response to controls and turbulence. Improving the ride quality of the vehicle and raising the flutter boundary of the aerodynamically-heated vehicle up to that of the cold vehicle were the objectives of the control law design investigations.
Document ID
19900018409
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Heeg, Jennifer
(NASA Langley Research Center Hampton, VA., United States)
Gilbert, Michael G.
(NASA Langley Research Center Hampton, VA., United States)
Pototzky, Anthony S.
(Lockheed Engineering and Sciences Co. Hampton, VA., United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1990
Subject Category
Aircraft Stability And Control
Report/Patent Number
NASA-TM-102713
NAS 1.15:102713
Report Number: NASA-TM-102713
Report Number: NAS 1.15:102713
Meeting Information
Meeting: AIAA Guidance, Navigation and Control Conference
Location: Portland, OR
Country: United States
Start Date: August 20, 1990
End Date: August 22, 1990
Accession Number
90N27725
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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