Development and Evaluation of an Integrated Flight and Propulsion Control System
Author : P.D. Shaw
Publisher :
Page : 14 pages
File Size : 47,84 MB
Release : 1985
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Author : P.D. Shaw
Publisher :
Page : 14 pages
File Size : 47,84 MB
Release : 1985
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Author : K. L. Smith
Publisher :
Page : 0 pages
File Size : 44,84 MB
Release : 1985
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Author : James F. Stewart
Publisher :
Page : 32 pages
File Size : 42,25 MB
Release : 1992
Category : Airplanes
ISBN :
Author : James F. Stewart
Publisher :
Page : 32 pages
File Size : 18,33 MB
Release : 1992
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Author : Walter C. Merrill
Publisher :
Page : 18 pages
File Size : 17,41 MB
Release : 1995
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Author :
Publisher :
Page : 32 pages
File Size : 30,18 MB
Release : 1990
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Author : Frank W. Burcham
Publisher :
Page : 32 pages
File Size : 17,95 MB
Release : 1990
Category : Airplanes
ISBN :
Author : Duane Loren Mattern
Publisher :
Page : 26 pages
File Size : 13,61 MB
Release : 1992
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Propulsion-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 :
Publisher :
Page : 30 pages
File Size : 12,90 MB
Release : 1997
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A state-of-the-art computational facility for aircraft flight control design, evaluation, and integration called CONDUIT (Control Designer's Unified Interface) has been developed. This paper describes the CONDUIT tool and case study applications to complex rotary- and fixed- wing fly-by-wire flight control problems. Control system analysis and design optimization methods are presented, including definition of design specifications and system models within CONDUIT, and the multi-objective function optimization (CONSOL-OPTCAD) used to tune the selected design parameters. Design examples are based on flight test programs for which extensive data are available for validation. CONDUIT is used to analyze baseline control laws against pertinent military handling qualities and control system specifications. In both case studies, CONDUIT successfully exploits trade-offs between forward loop and feedback dynamics to significantly improve the expected handling qualities and minimize the required actuator authority. The CONDUIT system provides a new environment for integrated control system analysis and design, and has potential for significantly reducing the time and cost of control system flight test optimization.
Author : James F. Stewart
Publisher :
Page : 28 pages
File Size : 30,82 MB
Release : 1992
Category : Airplanes
ISBN :