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Classical and modern control design of a speed-hold system for a STOL airplaneA speed-hold system for an experimental short takeoff and landing jet airplane has been designed using both classical root-locus and modern optimal control synthesis techniques. The purpose of the speed-hold system is to maintain airspeed during final approach in the presence of wind shears, gusts, engine failures, and pilot control inputs. Designs were based on using airspeed as a single measurement and two symmetrically deployed upper surface blown flaps as a single control. An optimal control law feeding back all the states and the integral of airspeed through constant gains provided superior performance in terms of speed tracking and control surface activity. However, when a constant-gain Kalman filter was inserted to estimate the states using only the measurement of airspeed, the performance of the optimal control law was reduced to the same as that of a much simpler classical proportional-path plus integral-path control law. To improve the performance of the optimal control law, additional measurements would be required.
Document ID
19810036137
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Blight, J. D.
(Boeing Commercial Airplane Co. Seattle, WA, United States)
Gangsaas, D.
(Boeing Commercial Airplane Co. Seattle, Wash., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 81-0017
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: St. Louis, MO
Start Date: January 12, 1981
End Date: January 15, 1981
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
81A20541
Funding Number(s)
CONTRACT_GRANT: NAS2-9081
Distribution Limits
Public
Copyright
Other

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