GLTRS--Glenn
TITLE AND SUBTITLE:
High Stability Engine Control (HISTEC) Flight Test Results

AUTHOR(S):
Robert D. Southwick, George W. Gallops, Laura J. Kerr, Robert P. Kielb, Mark G. Welsh, John C. DeLaat, and John S. Orme

REPORT DATE:
July 1998

FUNDING NUMBERS:
WU-523-53-13-00

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Lewis Research Center
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-11255

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-1998-208481
AIAA-98-3757

SUPPLEMENTARY NOTES:
Prepared for the 34th Joint Propulsion Conference cosponsored by AIAA, ASME, SAE, and ASEE, Cleveland, Ohio,
July 12-15, 1998. R.D. Southwick, G.W. Gallops, L.J. Kerr, R.P. Kielb, and M.G. Welsh, Pratt & Whitney, West Palm Beach, Florida 33410-9600; J.C. DeLaat, NASA Lewis Research Center; J.S. Orme, NASA Dryden Flight Research Center, Edwards, California. Responsible person, J.C. DeLaat, organization code 5530, (216) 433-3744.

ABSTRACT:
The High Stability Engine Control (HISTEC) Program, managed and funded by the NASA Lewis Research Center, is a cooperative effort between NASA and Pratt & Whitney (P&W). The program objective is to develop and flight demonstrate an advanced high stability integrated engine control system that uses real-time, measurementbased estimation of inlet pressure distortion to enhance engine stability. Flight testing was performed using the NASA Advanced Controls Technologies for Integrated Vehicles (ACTIVE) F-15 aircraft at the NASA Dryden Flight Research Center. The flight test configuration, details of the research objectives, and the flight test matrix to achieve those objectives are presented. Flight test results are discussed that show the design approach can accurately estimate distortion and perform realtime control actions for engine accommodation.

SUBJECT TERMS:
Aircraft engines; Engine control; Flow distortion; Stability; Augmentation

NUMBER OF PAGES:
15

PDF AVAILABLE FROM URL:
1998/TM-1998-208481.pdf
(1,075,722 KB)
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