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The Influence of Feedback on the Aeroelastic Behavior of Tilt Proprotor Aircraft Including the Effects of Fuselage MotionThe influence of single loop feedbacks to improve the stability of the system are considered. Reduced order dynamic models are employed where appropriate to promote physical insight. The influence of fuselage freedom on the aeroelastic stability, and the influence of the airframe flexibility on the low frequency modes of motion relevant to the stability and control characteristics of the vehicle were examined.
Document ID
19790018954
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Curtiss, H. C., Jr. (Princeton Univ. NJ, United States)
Komatsuzaki, T. (Princeton Univ. NJ, United States)
Traybar, J. J. (Princeton Univ. NJ, United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1979
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
NASA-CR-158778
TR-1441
Report Number: NASA-CR-158778
Report Number: TR-1441
Accession Number
79N27125
Funding Number(s)
CONTRACT_GRANT: NSG-2181
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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