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Candidate control design metrics for an agile fighterSuccess in the fighter combat environment of the future will certainly demand increasing capability from aircraft technology. These advanced capabilities in the form of superagility and supermaneuverability will require special design techniques which translate advanced air combat maneuvering requirements into design criteria. Control design metrics can provide some of these techniques for the control designer. Thus study presents an overview of control design metrics and investigates metrics for advanced fighter agility. The objectives of various metric users, such as airframe designers and pilots, are differentiated from the objectives of the control designer. Using an advanced fighter model, metric values are documented over a portion of the flight envelope through piloted simulation. These metric values provide a baseline against which future control system improvements can be compared and against which a control design methodology can be developed. Agility is measured for axial, pitch, and roll axes. Axial metrics highlight acceleration and deceleration capabilities under different flight loads and include specific excess power measurements to characterize energy meneuverability. Pitch metrics cover both body-axis and wind-axis pitch rates and accelerations. Included in pitch metrics are nose pointing metrics which highlight displacement capability between the nose and the velocity vector. Roll metrics (or torsion metrics) focus on rotational capability about the wind axis.
Document ID
19910008802
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Murphy, Patrick C. (NASA Langley Research Center Hampton, VA., United States)
Bailey, Melvin L. (Lockheed Engineering and Sciences Co. Hampton, VA., United States)
Ostroff, Aaron J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1991
Subject Category
Aircraft Stability And Control
Report/Patent Number
NAS 1.15:4238
L-16766
NASA-TM-4238
Accession Number
91N18115
Funding Number(s)
PROJECT: RTOP 505-66-71-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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