Integrated Airframe Propulsion Control
Author: Robert E. Fennell
Publisher:
Published: 1982
Total Pages: 106
ISBN-13:
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Author: Robert E. Fennell
Publisher:
Published: 1982
Total Pages: 106
ISBN-13:
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Publisher:
Published: 1990
Total Pages: 262
ISBN-13:
DOWNLOAD EBOOKAuthor: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-07-24
Total Pages: 264
ISBN-13: 9781723555251
DOWNLOAD EBOOKThe design of an integrated airframe/propulsion control system architecture is described. The design is based on a prevalidation methodology that uses both reliability and performance. A detailed account is given for the testing associated with a subset of the architecture and concludes with general observations of applying the methodology to the architecture. Cohen, Gerald C. and Lee, C. William and Strickland, Michael J. and Torkelson, Thomas C. Unspecified Center NASA-CR-182007, NAS 1.26:182007 NAS1-18099; RTOP 505-66-71-02...
Author:
Publisher:
Published: 1990
Total Pages: 32
ISBN-13:
DOWNLOAD EBOOKAuthor: Walter C. Merrill
Publisher:
Published: 1995
Total Pages: 18
ISBN-13:
DOWNLOAD EBOOKAuthor: Robert E. Fennell
Publisher:
Published: 1982
Total Pages: 116
ISBN-13:
DOWNLOAD EBOOKAuthor: Duane Loren Mattern
Publisher:
Published: 1992
Total Pages: 26
ISBN-13:
DOWNLOAD EBOOKPropulsion-system-specific results are presented from the application of the integrated methodology for propulsion and airframe control (IMPAC) design approach to integrated flight/propulsion control design for a 'short takeoff and vertical landing' (STOVL) aircraft in transition flight. The IMPAC method is briefly discussed and the propulsion system specifications for the integrated control design are examined. The structure of a linear engine controller that results from partitioning a linear centralized controller is discussed. The details of a nonlinear propulsion control system are presented, including a scheme to protect the engine operational limits: the fan surge margin and the acceleration/deceleration schedule that limits the fuel flow. Also, a simple but effective multivariable integrator windup protection scheme is examined. Nonlinear closed-loop simulation results are presented for two typical pilot commands for transition flight: acceleration while maintaining flightpath angle and a change in flightpath angle while maintaining airspeed. The simulation nonlinearities include the airframe/engine coupling, the actuator and sensor dynamics and limits, the protection scheme for the engine operational limits, and the integrator windup protection. Satisfactory performance of the total airframe plus engine system for transition flight, as defined by the specifications, was maintained during the limit operation of the closed-loop engine subsystem.
Author: James F. Stewart
Publisher:
Published: 1992
Total Pages: 32
ISBN-13:
DOWNLOAD EBOOKAuthor: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
Published: 2018-07-17
Total Pages: 144
ISBN-13: 9781722979188
DOWNLOAD EBOOKThe major contribution of this research was the exposition of the fact that airframe and engine interactions could be present, and their effects could include loss of stability and performance of the control systems. Also, the significance of two directional, as opposed to one-directional, coupling was identified and explained. A multivariable stability and performance analysis methodology was developed, and applied to several candidate aircraft configurations. In these example evaluations, the significance of these interactions was underscored. Also exposed was the fact that with interactions present along with some integrated control approaches, the engine command/limiting logic (which represents an important nonlinear component of the engine control system) can impact closed-loop airframe/engine system stability. Finally, a brief investigation of control-law synthesis techniques appropriate for the class of systems was pursued, and it was determined that multivariable techniques, including model-following formulations of LQG and/or H infinity methods, showed promise. However, for practical reasons, decentralized control architectures are preferred, which is an architecture incompatible with these synthesis methods. The major contributions of the second phase of the grant was the development of conditions under which no decentralized controller could achieve closed loop system requirements on stability and/or performance. Sought were conditions that depended only on properties of the plant and the requirement, and independent of any particular control law or synthesis approach. Therefore, they could be applied a priori, before synthesis of a candidate control law. Under this grant, such conditions were found regarding stability, and encouraging initial results were obtained regarding performance. Schmidt, David K. and Schierman, John D. Unspecified Center AIRCRAFT STABILITY; AIRFRAMES; CONTROL THEORY; CONTROLLABILITY; ENGINE AIRFRAME INTEGRATION; ENGINE CONTROL; F...
Author: James F. Stewart
Publisher:
Published: 1992
Total Pages: 32
ISBN-13:
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