A Linear Quadratic Regulator synthesis technique was used to design an explicit model following control system for the Oblique Wing Research Aircraft (OWRA). The forward path model (Maneuver Command Generator) was designed to incorporate the desired flying qualities and response decoupling. The LQR synthesis was based on the use of generalized controls, and it was structured to provide a proportional/integral error regulator with feedforward compensation. An unexpected consequence of this design approach was the ability to decouple the control synthesis into separate longitudinal and lateral directional designs. Longitudinal and lateral directional control laws were generated for each of the nine design flight conditions, and gain scheduling requirements were addressed. A fully coupled 6 degree of freedom open loop model of the OWRA along with the longitudinal and lateral directional control laws was used to assess the closed loop performance of the design. Evaluations were performed for each of the nine design flight conditions.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Application of modern control design methodology to oblique wing research aircraft


    Beteiligte:

    Erscheinungsdatum :

    1991-07-01


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Oblique Wing Aircraft

    Torenbeek, Egbert | Wiley | 2020



    Wing Design of an Oblique Wing Combat Aircraft

    Nangia, R.K. / Greenwell, D.I. / International Council of the Aeronautical Sciences | British Library Conference Proceedings | 2000


    Oblique rotor-wing aircraft

    COMBS CORY MICHAEL | Europäisches Patentamt | 2019

    Freier Zugriff

    OBLIQUE ROTOR-WING AIRCRAFT

    COMBS CORY MICHAEL | Europäisches Patentamt | 2018

    Freier Zugriff