Adaptive Fuel Control Feasibility Investigation for Helicopter Applications PUBLIC ACCESS

[+] Author Affiliations
T. Morrison, R. D. Zagranski

Chandler Evans Inc., West Hartford, CT

J. J. Howlett

Sikorsky Aircraft, Stratford, CT

Paper No. 82-GT-205, pp. V002T02A011; 11 pages
  • ASME 1982 International Gas Turbine Conference and Exhibit
  • Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery
  • London, England, April 18–22, 1982
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7957-3
  • Copyright © 1982 by ASME


A United States Army-sponsored, computer-aided study of a twin engine helicopter is being conducted to determine the feasibility of incorporating into the engine microprocessor-based control system, airframe signals and control strategies that improve helicopter capability. Investigations are considering on-line changes to the control characteristics which adapt to abnormal engine operation due, for example, to engine deterioration, surge or failure. The anticipation of power recovery from a split needle condition is accomplished with rotor speed feedback which allows increased transient load factors and improved handling qualities in maneuvering flight. For minimum fuel consumption in cruise, the control will seek the optimum rotor speed. An improvement in torsional damping is achieved with software filters which reduce the dependability of the drive train stability on the blade lag dampers. Studies to date indicate that there may be substantial payback in implementing these new control features.

Copyright © 1982 by ASME
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