This paper presents a summary of a series of recent analytical studies conducted to investigate one-engine-inoperative (OEI) optimal control strategies and the associated optimal trajectories for a twin engine helicopter in Category-A terminal-area operations. These studies also examine the associated heliport size requirements and the maximum gross weight capability of the helicopter. Using an eight states, two controls, augmented point-mass model representative of the study helicopter, continued takeoff (CTO), rejected takeoff (RTO), balked landing (BL), and continued landing (CL) are investigated for both vertical-takeoff-and-landing (VTOL) and short-takeoff-and-landing (STOL) terminal-area operations. The formulation of the non-linear optimal control problems with considerations for realistic constraints, solution methods for the two-point boundary-value problem, a new real-time generation method for the optimal OEI trajectories, and the main results of this series of trajectory optimization studies are presented. In particular, a new balanced-weight concept for determining the takeoff decision point for VTOL Category-A operations is proposed, extending the balanced-field length concept used for STOL operations.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Optimal trajectories for the helicopter in one-engine-inoperative terminal-area operations


    Weitere Titelangaben:

    Optimale Flugbahnen für den Hubschrauber mit einem nicht arbeitenden Triebwerk im Flugplatzbetrieb


    Beteiligte:
    Chen, R.T.N. (Autor:in) / Zhao, Y. (Autor:in)


    Erscheinungsdatum :

    1996


    Format / Umfang :

    27 Seiten, 16 Bilder, 1 Tabelle, 40 Quellen



    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch







    Optimal Trajectories for the Helicopter in One-Engine-Inoperative Terminal-Area Operations

    Chen, R. T. N. / Zhao, Y. / Advisory Group for Aerospace Research and Development; Flight Vehicle Integration Panel | British Library Conference Proceedings | 1997