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  • 1
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    Dynamics and control (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Dynamics and control of supersonic propulsion systems
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 351-395
    Format: text
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  • 2
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    Optimal control of a supersonic inlet to minimize frequency of inlet unstart (1978)
    In:  CASI
    Details
    Publication Date: 2006-03-02
    Description: A preliminary investigation into the use of modern control theory for the design of controls for a supersonic inlet is described. In particular, the task of controlling a mixed-compression supersonic inlet is formulated as a linear optimal stochastic control and estimation problem. An inlet can exhibit an undesirable instability due to excessive inlet normal shock motion. For the optimal control formulation of the inlet problem, a non quadratic performance index, which is equal to the expected frequency of inlet unstarts, is used. This physically meaningful performance index is minimized for a range of inlet disturbance and measurement noise covariances.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA, Washington Fourth Inter-Center Control Systems Conf.; p 323-335
    Format: text
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  • 3
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    Fast response electrohydraulic servo system (1970)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Electrohydraulic fast response servosystem design and operation, describing nonlinear model based on component limitations
    Keywords: AUXILIARY SYSTEMS
    Type: ; UGREVUE(
    Format: text
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  • 4
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    Application of quadratic optimization to supersonic inlet control. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: This paper describes the application of linear stochastic optimal control theory to the design of the control system for the air intake, the inlet, of a supersonic air-breathing propulsion system. The controls must maintain a stable inlet shock position in the presence of random airflow disturbances and prevent inlet unstart. Two different linear time invariant controllers are developed. One is designed to minimize a nonquadratic index, the expected frequency of inlet unstart, and the other is designed to minimize the mean square value of inlet shock motion. The quadratic equivalence principle is used to obtain a linear controller that minimizes the nonquadratic index. The two controllers are compared on the basis of unstart prevention, control effort requirements, and frequency response. It is concluded that while controls designed to minimize unstarts are desirable in that the index minimized is physically meaningful, computation time required is longer than for the minimum mean square shock position approach. The simpler minimum mean square shock position solution produced expected unstart frequency values which were not significantly larger than those of the nonquadratic solution.
    Keywords: AIRCRAFT
    Type: Automatica; 8; Sept
    Format: text
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  • 5
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    A digital computer propulsion control facility: Description of capabilities and summary of experimental program results (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Flight weight digital computers are being used today to carry out many of the propulsion system control functions previously delegated exclusively to hydromechanical controllers. An operational digital computer facility for propulsion control mode studies has been used successfully in several experimental programs. This paper describes the system and some of the results concerned with engine control, inlet control, and inlet engine integrated control. Analytical designs for the digital propulsion control modes include both classical and modern/optimal techniques.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: Advanced Control Technol. and its Potential for Future Transport Aircraft; p 477-501
    Format: application/pdf
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  • 6
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    Control technology for future aircraft propulsion systems (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The need for a more sophisticated engine control system is discussed. The improvements in better thrust-to-weight ratios demand the manipulation of more control inputs. New technological solutions to the engine control problem are practiced. The digital electronic engine control (DEEC) system is a step in the evolution to digital electronic engine control. Technology issues are addressed to ensure a growth in confidence in sophisticated electronic controls for aircraft turbine engines. The need of a control system architecture which permits propulsion controls to be functionally integrated with other aircraft systems is established. Areas of technology studied include: (1) control design methodology; (2) improved modeling and simulation methods; and (3) implementation technologies. Objectives, results and future thrusts are summarized.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-14 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 231-247
    Format: application/pdf
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  • 7
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    Investigation of a nozzle instability on an F100 engine equipped with a digital electronic engine control (1984)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An instability in the nozzle of the F100 engine, equipped with a digital electronic engine control (DEEC), was observed during a flight evaluation on an F-15 aircraft. The instability occurred in the upper left hand corner (ULMC) of the flight envelope during augmentation. The instability was not predicted by stability analysis, closed-loop simulations of the the engine, or altitude testing of the engine. The instability caused stalls and augmentor blowouts. The nozzle instability and the altitude testing are described. Linear analysis and nonlinear digital simulation test results are presented. Software modifications on further flight test are discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: PAPER-12 , Digital Electronic Engine Control (DEEC) Flight Evaluation in an F-15 Airplane; p 201-214
    Format: application/pdf
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  • 8
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    Propulsion control and control theory: A new research focus (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Technological developments necessary for the implementation of advanced digital control concepts for aircraft propulsion are identified and discussed. Developments associated with the replacement analog controllers with digital control systems, sensors and actuators, and control modes and software are reported.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Propulsion Controls, 1979; p 89-95
    Format: application/pdf
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  • 9
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    Optimal control of supersonic inlets to minimize unstarts (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Design and characteristics of supersonic inlet controls for minimizing inlet unstarts
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6408 , E-6253
    Format: application/pdf
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  • 10
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    Dynamic performance analysis of a fuel-control valve for use in airbreathing engine research (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Dynamic performance analysis of fast-response fuel control valve for air breathing engine research
    Keywords: AUXILIARY SYSTEMS
    Type: NASA-TN-D-5331
    Format: application/pdf
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