The application of computer programs for the analysis and synthesis of optimal aircraft designs to the problem of optimal controls design is dealt with. The mathematical model of aircraft motion is described. An equations system related to the linearized equations of motion was set up and the necessary optimality conditions formulated. The approximation of aerodynamic and propulsion characteristics is discussed, and an approximation by rational functions is proposed. Two highly developed, fast optimization algorithms are presented, a multitarget and a collocation method. Methods for determining estimated values are outlined. Results of numerical calculations for time and fuel optimized trajectories of two high performance aircraft are presented.


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    Title :

    Optimal Level Controls of High Performance Aircraft Optimale Ebene Steuerungen von Hochleistungsflugzeugen


    Contributors:
    D. Kraft (author) / G. C. Shau (author) / K. H. Well (author) / E. Berger (author)

    Publication date :

    1977


    Size :

    53 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English