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A dynamic analysis of the motion of a low-wing general aviation aircraft about its calculated equilibrium flat spin modeThe properties of the flat spin mode of a general aviation configuration have been studied through analysis of rotary balance data, numerical simulation, and analytical study of the equilibrium state. The equilibrium state is predicted well from rotary balance data. The variations of yawing moment and pitching moment as functions of sideslip have been shown to be of great importance in obtaining accurate modeling. These dependencies are not presently available with sufficient accuracy from previous tests or theories. The stability of the flat spin mode has been examined extensively using numerical linearization, classical perturbation methods, and reduced order modeling. The stability exhibited by the time histories and the eigenvalue analyses is shown to be strongly dependent on certain static cross derivatives and more so on the dynamic derivatives. Explicit stability criteria are obtained from the reduced order models.
Document ID
19800061694
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Tischler, M. B.
(Systems Technology, Inc. Hawthorne, Calif., United States)
Barlow, J. B.
(Maryland, University College Park, Md., United States)
Date Acquired
August 10, 2013
Publication Date
January 1, 1980
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 80-1565
Meeting Information
Meeting: Atmospheric Flight Mechanics Conference
Location: Danvers, MA
Start Date: August 11, 1980
End Date: August 13, 1980
Accession Number
80A45864
Funding Number(s)
CONTRACT_GRANT: NSG-1570
Distribution Limits
Public
Copyright
Other

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