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  • AIRCRAFT PROPULSION AND POWER  (3)
  • OPTICS
  • 1990-1994  (4)
  • 1991  (4)
  • 1
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    Fiber Optic Tactical Local Network (FOTLAN) (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A 100 Mbit/s FDDI (fiber distributed data interface) network interface unit is described that supports real-time data, voice and video. Its high-speed interrupt-driven hardware architecture efficiently manages stream and packet data transfer to the FDDI network. Other enhancements include modular single-mode laser-diode fiber optic links to maximize node spacing, optic bypass switches for increased fault tolerance, and a hardware performance monitor to gather real-time network diagnostics.
    Keywords: OPTICS
    Type: NASA, Washington, Technology 2000, Volume 2; p 268-275
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Preliminary flight evaluation of an engine performance optimization algorithm (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: A performance-seeking control (PSC) algorithm has undergone initial flight test evaluation in subsonic operation of a PW 1128-engined F-15; this algorithm is designed to optimize the quasi-steady performance of an engine for three primary modes: (1) minimum fuel consumption, (2) minimum fan-turbine inlet temperature (FTIT), and (3) maximum thrust. The flight test results have verified a thrust-specific fuel consumption reduction of 1 percent, up to 100 R decreases in FTIT, and increases of as much as 12 percent in maximum thrust. PSC technology promises to be of value in next-generation tactical and transport aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 91-1998
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    A simulation study of turbofan engine deterioration estimation using Kalman filtering techniques (1991)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Deterioration of engine components may cause off-normal engine operation. The result is an unecessary loss of performance, because the fixed schedules are designed to accommodate a wide range of engine health. These fixed control schedules may not be optimal for a deteriorated engine. This problem may be solved by including a measure of deterioration in determining the control variables. These engine deterioration parameters usually cannot be measured directly but can be estimated. A Kalman filter design is presented for estimating two performance parameters that account for engine deterioration: high and low pressure turbine delta efficiencies. The delta efficiency parameters model variations of the high and low pressure turbine efficiencies from nominal values. The filter has a design condition of Mach 0.90, 30,000 ft altitude, and 47 deg power level angle (PLA). It was evaluated using a nonlinear simulation of the F100 engine model derivative (EMD) engine, at the design Mach number and altitude over a PLA range of 43 to 55 deg. It was found that known high pressure turbine delta efficiencies of -2.5 percent and low pressure turbine delta efficiencies of -1.0 percent can be estimated with an accuracy of + or - 0.25 percent efficiency with a Kalman filter. If both the high and low pressure turbine are deteriorated, the delta efficiencies of -2.5 percent to both turbines can be estimated with the same accuracy.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-104233 , H-1616 , NAS 1.15:104233
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Preliminary flight evaluation of an engine performance optimization algorithm (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A performance seeking control (PSC) algorithm has undergone initial flight test evaluation in subsonic operation of a PW 1128 engined F-15. This algorithm is designed to optimize the quasi-steady performance of an engine for three primary modes: (1) minimum fuel consumption; (2) minimum fan turbine inlet temperature (FTIT); and (3) maximum thrust. The flight test results have verified a thrust specific fuel consumption reduction of 1 pct., up to 100 R decreases in FTIT, and increases of as much as 12 pct. in maximum thrust. PSC technology promises to be of value in next generation tactical and transport aircraft.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-4328 , H-1745 , NAS 1.15:4328 , Joint Propulsion Conference; Jun 24, 1991 - Jun 26, 1991; Sacramento, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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