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  • 1
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    Integrated flight/propulsion control system design based on a centralized approach (1991)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: Journal of Guidance, Control, and Dynamics (ISSN 0731-5090); 14; 107-116
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Application of an integrated flight/propulsion control design methodology to a STOVL aircraft (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The application of an emerging Integrated Flight/Propulsion Control design methodology to a STOVL aircraft in transition flight is reported. The methodology steps consist of: (1) design of a centralized feedback controller to provide command tracking and stability and performance robustness considering the fully integrated airframe/propulsion model as one high-order system; (2) partition of the centralized controller into a decentralized, hierarchical form compatible with implementation requirements; and (3) design of command shaping prefilters from pilot control effectors to commanded variables to provide the overall desired response to pilot inputs. Intermediate design results using this methodology are presented, the complete point control design with the propulsion system operating schedule and limit protection logic included is evaluated for sample pilot control inputs, and the response is compared with that of an 'ideal response model' derived from Level I handling qualities requirements.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 91-2792
    Format: text
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  • 3
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    Distributed simulation using a real-time shared memory network (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The Advanced Control Technology Branch of the NASA Lewis Research Center performs research in the area of advanced digital controls for aeronautic and space propulsion systems. This work requires the real-time implementation of both control software and complex dynamical models of the propulsion system. We are implementing these systems in a distributed, multi-vendor computer environment. Therefore, a need exists for real-time communication and synchronization between the distributed multi-vendor computers. A shared memory network is a potential solution which offers several advantages over other real-time communication approaches. A candidate shared memory network was tested for basic performance. The shared memory network was then used to implement a distributed simulation of a ramjet engine. The accuracy and execution time of the distributed simulation was measured and compared to the performance of the non-partitioned simulation. The ease of partitioning the simulation, the minimal time required to develop for communication between the processors and the resulting execution time all indicate that the shared memory network is a real-time communication technique worthy of serious consideration.
    Keywords: COMPUTER OPERATIONS AND HARDWARE
    Type: NASA-TM-106239 , E-7969 , NAS 1.15:106239 , AVSCOM-TR-92-C-020 , AD-A268827
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Using Neural Networks for Sensor Validation (1998)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents the results of applying two different types of neural networks in two different approaches to the sensor validation problem. The first approach uses a functional approximation neural network as part of a nonlinear observer in a model-based approach to analytical redundancy. The second approach uses an auto-associative neural network to perform nonlinear principal component analysis on a set of redundant sensors to provide an estimate for a single failed sensor. The approaches are demonstrated using a nonlinear simulation of a turbofan engine. The fault detection and sensor estimation results are presented and the training of the auto-associative neural network to provide sensor estimates is discussed.
    Keywords: Aircraft Instrumentation
    Type: NASA/TM-1998-208483 , E-11258 , NAS 1.15:208483 , AIAA Paper 98-3547 , Joint Propulsion Conference; Jul 12, 1998 - Jul 15, 1998; Cleveland, OH; United States
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  • 5
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    Integrated flight/propulsion control system design based on a centralized approach (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: An integrated flight/propulsion control system design is presented for the piloted longitudinal landing task with a modern, statically unstable, fighter aircraft. A centralized compensator based on the Linear Quadratic Gaussian/Loop Transfer Recovery methodology is first obtained to satisfy the feedback loop performance and robustness specificiations. This high-order centralized compensator is then partitioned into airframe and engine sub-controllers based on modal controllability/observability for the compensator modes. The order of the sub-controllers is then reduced using internally-balanced realization techniques and the sub-controllers are simplified by neglecting the insignificant feedbacks. These sub-controllers have the advantage that they can be implemented as separate controllers on the airframe and the engine while still retaining the important performance and stability characteristics of the full-order centralized compensator. Command prefilters are then designed for the closed-loop system with the simplified sub-controllers to obtain the desired system response to airframe and engine command inputs, and the overall system performance evaluation results are presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-102137 , E-4860 , NAS 1.15:102137 , AIAA PAPER 89-3520 , Guidance, Navigation and Control Conference; Aug 14, 1989 - Aug 16, 1989; Boston, MA; United States
    Format: application/pdf
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  • 6
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    Forced response testing of an axi-centrifugal turboshaft engine (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Dynamic data from tests of a T55-L-712 engine are presented. Engine stall/surge data were analyzed using digital signal processing techniques. In addition, forced response testing (system identification studies) was done at various engine speeds. Forced response testing was done using eight jet ejectors approximately equally circumferentially spaced about the compressor front face. This paper presents some preliminary results for the ground idle (approximately 60% of design speed) point. Brief descriptions of the jet injection system, the test matrix, and analysis techniques used are presented. Results of these analyses indicate a substantial transfer of energy across the compressor first stage at some frequencies and that the ejectors are effective in modifying the local flow conditions in front of the first compressor stage.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-107282 , NAS 1.15:107282 , AIAA Paper 96-2573 , E-10357 , ARL-TR-1151 , Joint Propulsion Conference; Jul 01, 1996 - Jul 03, 1996; Lake Buena Vista, FL; United States
    Format: application/pdf
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  • 7
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    IMPAC - An integrated methodology for propulsion and airframe control (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The NASA Lewis Research Center approach to developing integrated flight propulsion control (IFPC) technologies is an in-house research program referred to as IMPAC-Integrated Methodology for Propulsion and Airframe Control. The goals of IMPAC are to develop a viable alternative to the existing integrated control design methodologies that will allow for improved system performance and simplicity of control law synthesis and implementation, and to demonstrate the applicability of the methodology to a supersonic STOVL fighter aircraft. An overview of IMPAC is presented, including a detailed discussion of the various important design and evaluation steps in the methodology.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: 1991 American Control Conference; Jun 26, 1991 - Jun 28, 1991; Boston, MA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 8
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    Application of an integrated flight/propulsion control design methodology to a STOVL aircraft (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results are presented from the application of an emerging Integrated Flight/Propulsion Control (IFPC) design methodology to a Short Take Off and Vertical Landing (STOVL) aircraft in transition flight. The steps in the methodology consist of designing command shaping prefilters to provide the overall desired response to pilot command inputs. A previously designed centralized controller is first validated for the integrated airframe/engine plant used. This integrated plant is derived from a different model of the engine subsystem than the one used for the centralized controller design. The centralized controller is then partitioned in a decentralized, hierarchical structure comprising of airframe lateral and longitudinal subcontrollers and an engine subcontroller. Command shaping prefilters from the pilot control effector inputs are then designed and time histories of the closed loop IFPC system response to simulated pilot commands are compared to desired responses based on handling qualities requirements. Finally, the propulsion system safety and nonlinear limited protection logic is wrapped around the engine subcontroller and the response of the closed loop integrated system is evaluated for transients that encounter the propulsion surge margin limit.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-105254 , E-6583 , NAS 1.15:105254 , AIAA PAPER 91-2792 , Guidance, Navigation and Control Conference; Aug 12, 1991 - Aug 14, 1991; New Orleans, LA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Integrated flight/propulsion control system design based on a centralized approach (1989)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: An integrated flight/propulsion control system design is presented for the piloted longitudinal landing task with a modern, statically unstable, fighter aircraft. A centralized compensator based on the Linear Quadratic Gaussian/Loop Transfer Recovery methodology is first obtained to satisfy the feedback loop performance and robustness specificiations. This high-order centralized compensator is then partitioned into airframe and engine sub-controllers based on modal controllability/observability for the compensator modes. The order of the sub-controllers is then reduced using internally-balanced realization techniques and the sub-controllers are simplified by neglecting the insignificant feedbacks. These sub-controllers have the advantage that they can be implemented as separate controllers on the airframe and the engine while still retaining the important performance and stability characteristics of the full-order centralized compensator. Command prefilters are then designed for the closed-loop system with the simplified sub-controllers to obtain the desired system response to airframe and engine command inputs, and the overall system performance evaluation results are presented.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 89-3520 , AIAA Guidance, Navigation and Control Conference; Aug 14, 1989 - Aug 16, 1989; Boston, MA; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Comparisons of Rig and Engine Dynamic Events in the Compressor of an Axi-Centrifugal Turboshaft Engine (1996)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Steady state and dynamic data were acquired in a T55-L-712 compressor rig. In addition, a T55-L-12 engine was instrumented and similar data were acquired. Rig and engine stall/surge data were analyzed using modal techniques. This paper compares rig and engine preliminary results for the ground idle (approximately 60% of design speed) point. The results of these analyses indicate both rig and engine dynamic event are preceded by indications of traveling wave energy in front of the compressor face. For both rig and engine, the traveling wave energy contains broad band energy with some prominent narrow peaks and, while the events are similar in many ways, some noticeable differences exist between the results of the analyses of rig data and engine data.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-107339 , NAS 1.15:107339 , ASME-96-GT-239 , ARL-TR-1108 , E-10478 , Gas Turbine and Aeroengine Congress; Jun 10, 1996 - Jun 13, 1996; Birmingham; United Kingdom
    Format: application/pdf
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