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Aircraft agility maneuversA new dynamic model for aircraft motions is presented. This model can be viewed as intermediate between a point-mass model, in which the body attitude angles are control-like, and a rigid-body model, in which the body-attitude angles evolve according to Newton's Laws. Specifically, consideration is given to the case of symmetric flight, and a model is constructed in which the body roll-rate and the body pitch-rate are the controls. In terms of this body-rate model a minimum-time heading change maneuver is formulated. When the bounds on the body-rates are large the results are similar to the point-mass model in that the model can very quickly change the applied forces and produce an acceleration to turn the vehicle. With finite bounds on these rates, the forces change in a smooth way. This leads to a measurable effect of agility.
Document ID
19920072734
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Cliff, Eugene M.
(NASA Langley Research Center Hampton, VA, United States)
Thompson, Brian G.
(Virginia Polytechnic Institute and State University Blacksburg, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 92-4489
Meeting Information
Meeting: AIAA Atmospheric Flight Mechanics Conference
Location: Hilton Head Island, SC
Country: United States
Start Date: August 10, 1992
End Date: August 12, 1992
Accession Number
92A55358
Funding Number(s)
CONTRACT_GRANT: NAG1-1405
CONTRACT_GRANT: F49620-92-J-0078
Distribution Limits
Public
Copyright
Other

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