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  • 1
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    Design of a multivariable integrated control for a supersonic propulsion system (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: An inlet/engine/nozzle integrated control mode for the propulsion system of an advanced supersonic commercial aircraft was studied. Results show that integration of these control functions can result in both operational and performance benefits for the propulsion system. For example, this integrated control mode may make it possible to minimize the use of inlet bypass doors for shock position control. This may be of benefit to the aircraft as a result of minimizing: (1) bypass bleed drag effects; (2) perturbations to the aircraft resulting from the side thrust effect of the bypass bleeds; and (3) potential unstarts of the inlet. A conceptual integrated control mode was developed which makes use of many cross coupling paths between inlet and engine control variables and inlet and engine sensed variables. A multivariable control design technique based upon linear quadratic regulator theory was applied to designing the feedback gains for this control to allow a simulation evaluation of the benefits of the integrated control mode.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Lewis Research Center Propulsion Controls, 1979; p 35-47
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Propulsion control technology (1984)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A brief discussion of digital jet engine control systems is given. Performance tests, systems integration, and redundancy are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA. Langley Research Center NASA Aircraft Controls Research, 1983; p 585-592
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    HYTESS: A hypothetical turbofan engine simplified simulation (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: A users manual for a hypothetical turbofan engine simplified simulation is presented. This digital simulation exists as FORTRAN source code. The program is self-contained and was developed to offer those interested in engine dynamics and controls research an efficient, realistic, and easily used engine simulation. The engine is modeled using a state space formulation. Matrix elements within the linear state space structure are nonlinear functions of various engine variables.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-83561 , E-1940 , NAS 1.15:83561
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Sensor failure detection system (1981)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Advanced concepts for detecting, isolating, and accommodating sensor failures were studied to determine their applicability to the gas turbine control problem. Five concepts were formulated based upon such techniques as Kalman filters and a screening process led to the selection of one advanced concept for further evaluation. The selected advanced concept uses a Kalman filter to generate residuals, a weighted sum square residuals technique to detect soft failures, likelihood ratio testing of a bank of Kalman filters for isolation, and reconfiguring of the normal mode Kalman filter by eliminating the failed input to accommodate the failure. The advanced concept was compared to a baseline parameter synthesis technique. The advanced concept was shown to be a viable concept for detecting, isolating, and accommodating sensor failures for the gas turbine applications.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-165515 , PWA-5736-17
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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