High stability engine control (HISTEC) flight test results
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High stability engine control (HISTEC) flight test results

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Published by National Aeronautics and Space Administration, Lewis Research Center, National Technical Information Service, distributor in [Cleveland, Ohio], [Springfield, Va .
Written in English


  • Engine control.,
  • F-15 aircraft.,
  • Flight tests.,
  • Aircraft engines.,
  • Flow distortion.,
  • Thrust control.

Book details:

Edition Notes

StatementRobert D. Southwick ... [et al.].
SeriesNASA/TM -- 1998-208481., NASA technical memorandum -- 208481.
ContributionsSouthwick, Robert D., Lewis Research Center.
The Physical Object
Pagination1 v.
ID Numbers
Open LibraryOL15544453M

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the NASA High Stability Engine Control (HISTEC) program. 3 Distortion estimation is accomplished with a limited number of high-response static pressure measurements at the engine face and a frequency-based reduction algorithm. The algorithm, known as the distortion estimation system (DES), predicts the loss of engine stability margin as a result of inlet distortion. 3. Additional Physical Format: Microfiche version: DeLaat, John C. High stability engine control (HISTEC) (OCoLC) Material Type: Document, Government . NASA is sponsoring the design, development, and flight demonstration of an advanced high stability integrated engine control system using real-time estimation of distortion to enhance engine stability. A HISTEC-enabled decrease in design stall margin requirements will significantly increase propulsion system performance and /or reduce weight. The High Stability Engine Control (HISTEC) program has developed technologies for an advanced, integrated engine control system that uses measurement- based estimates of distortion to enhance engine stability.

Historical Engine Control Engine shaft speed Fuel flow rate (Wf) or fuel ratio unit (Wf/P3) Required fuel flow @ steady state Max. flow limit Min. flow limit Idle power Max. power Proportional control gain or droop slope Droop slope Safe operating region GE I-A () • Fuel flow is the only controlled variable. - Hydro-mechanical governor. Low tails increase stability at high angles of attack but can also result in buffeting and non-linear control response during normal flight. High tails are generally necessary with rear-fuselage mounted engines and are restricted to high-speed military aircraft use. The rear-engine configuration has generally been superseded by under-wing. adaptable into an engine’s electronic control system. This real-time scheme for detecting compressor instabilities was demonstrated on both in a full-scale high-speed compressor rig test and in an advanced aircraft engine test. In the multi-stage advanced compressor rig test, the stability management system was. Vehicle stability control is a technology designed to arrest skids. The intention is to enable a driver to maintain control of a vehicle during sudden and/or abrupt changes of direction. The goal is t.

Static Longitudinal Stability and Control The most critical aspects of static longitudinal stability relate to control forces required for changing trim or performing maneuvers. Our textbook [1] treats primarily the situ-ation when the controls are fixed. This is, of course, and idealization, even for the case. The performance, stability, control and response of aircraft are key areas of aeronautical engineering. This book provides a comprehensive overview to the underlying theory and application of what are often perceived to be difficult topics. Flight Testing, Volume II: Stability and Control focuses on the development of adequate flight test techniques for the appraisal of stability and control characteristics and flying qualities of airplanes. This book . Don't show me this again. Welcome! This is one of over 2, courses on OCW. Find materials for this course in the pages linked along the left. MIT OpenCourseWare is a free & open publication of material from thousands of MIT courses, covering the entire MIT curriculum.. No enrollment or registration.