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  • 1990-1994  (9)
  • 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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    NASA TECHNICAL REPORTS
  • 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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    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
  • 5
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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
  • 6
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    H-infinity based integrated flight/propulsion control design for a STOVL aircraft in transition flight (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: This paper presents results from an application of H(infinity) control design methodology to a centralized integrated flight/propulsion control (IFPC) system design for a supersonic STOVL fighter aircraft in transition flight. The overall design methodology consists of a centralized IFPC design with controller partitioning. Design and evaluation vehicle models are summarized, and insight is provided into formulating the H(infinity) control problem such that it reflects the IFPC design objective. The H(infinity) controller is shown to provide decoupled command tracking for the design model. The controller order could be significantly reduced by modal residualization of the fast controller modes without any deterioration in performance.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AIAA PAPER 90-3335 , AIAA Guidance, Navigation and Control Conference; Aug 20, 1990 - Aug 22, 1990; Portland, OR; United States
    Format: text
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    NASA TECHNICAL REPORTS
  • 7
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    IMPAC: An Integrated Methodology for Propulsion and Airframe Control (1991)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The National Aeronautics and Space Administration is actively involved in the development of enabling technologies that will lead towards aircraft with new/enhanced maneuver capabilities such as Short Take-Off Vertical Landing (STOVL) and high angle of attack performance. Because of the high degree of dynamic coupling between the airframe and propulsion systems of these types of aircraft, one key technology is the integration of the flight and propulsion control. 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. Based on some preliminary control design studies that included evaluation of the existing methodologies, the IFPC design methodology that is emerging at the Lewis Research Center consists of considering the airframe and propulsion system as one integrated system for an initial centralized controller design and then partitioning the centralized controller into separate airframe and propulsion system subcontrollers to ease implementation and to set meaningful design requirements for detailed subsystem control design and evaluation. An overview of IMPAC is provided and detailed discussion of the various important design and evaluation steps in the methodology are included.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-103805 , E-6035 , NAS 1.15:103805 , American Control Conference; Jun 26, 1991 - Jun 28, 1991; Boston, MA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    H-infinity based integrated flight-propulsion control design for a STOVL aircraft in transition flight (1990)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Results are presented from an application of H-infinity control design methodology to a centralized integrated flight/propulsion control (IFPC) system design for a supersonic Short Take-Off and Vertical Landing (STOVL) fighter aircraft in transition flight. The overall design methodology consists of a centralized IFPC controller design with controller partitioning. Only the feedback controller design portion of the methodology is addressed. Design and evaluation vehicle models are summarized, and insight is provided into formulating the H-infinity control problem such that it reflects the IFPC design objectives. The H-infinity controller is shown to provide decoupled command tracking for the design model. The controller order could be significantly reduced by modal residualization of the fast controller modes without any deterioration in performance. A discussion is presented of the areas in which the controller performance needs to be improved, and ways in which these improvements can be achieved within the framework of an H-infinity based linear control design.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: NASA-TM-103198 , E-5594 , NAS 1.15:103198 , Guidance, Navigation and Control Conference; Aug 20, 1990 - Aug 22, 1990; Portland, OR; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Piloted Evaluation of an Integrated Methodology for Propulsion and Airframe Control Design (1994)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: An integrated methodology for propulsion and airframe control has been developed and evaluated for a Short Take-Off Vertical Landing (STOVL) aircraft using a fixed base flight simulator at NASA Lewis Research Center. For this evaluation the flight simulator is configured for transition flight using a STOVL aircraft model, a full nonlinear turbofan engine model, simulated cockpit and displays, and pilot effectors. The paper provides a brief description of the simulation models, the flight simulation environment, the displays and symbology, the integrated control design, and the piloted tasks used for control design evaluation. In the simulation, the pilots successfully completed typical transition phase tasks such as combined constant deceleration with flight path tracking, and constant acceleration wave-off maneuvers. The pilot comments of the integrated system performance and the display symbology are discussed and analyzed to identify potential areas of improvement.
    Keywords: AIRCRAFT STABILITY AND CONTROL
    Type: AD-A290207 , ARL-TR-519 , E-9149 , NAS 1.15:106741 , NASA-TM-106741 , Guidance, Navigation and Control Conference; Aug 01, 1994 - Aug 03, 1994; Scottsdale, AZ; United States
    Format: application/pdf
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