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.
Propulsion System Performance Resulting from an Integrated Flight/Propulsion Control Design
1992
22 pages
Report
Keine Angabe
Englisch
Aircraft , Aeronautics , Jet & Gas Turbine Engines , Aircraft control , Feedback control , Propulsion system performance , Stovl aircraft , Controllers , Fuel flow , Actuators , Airframes , Airspeed , Engine airframe integration , Flight characteristics , Nonlinear systems , Nonlinearity , Transition flight
Propulsion Control Design For A STOVL Integrated Flight/Propulsion Control System
British Library Conference Proceedings | 1993
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