The results were presented of a parametric study performed to determine the optimum wing geometry for a proposed space shuttle orbiter. The results of the study establish the minimum weight wing for a series of wing-fuselage combinations subject to constraints on aerodynamic heating, wing trailing edge sweep, and wing over-hang. The study consists of a generalized design evaluation which has the flexibility of arbitrarily varying those wing parameters which influence the vehicle system design and its performance. The study is structured to allow inputs of aerodynamic, weight, aerothermal, structural and material data in a general form so that the influence of these parameters on the design optimization process can be isolated and identified. This procedure displays the sensitivity of the system design of variations in wing geometry. The parameters of interest are varied in a prescribed fashion on a selected fuselage and the effect on the total vehicle weight is determined. The primary variables investigated are: wing loading, aspect ratio, leading edge sweep, thickness ratio, and taper ratio.


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    Titel :

    Wing optimization for space shuttle orbiter vehicles


    Beteiligte:
    Surber, T. E. (Autor:in) / Bornemann, W. E. (Autor:in) / Miller, W. D. (Autor:in)


    Erscheinungsdatum :

    1972-02-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :



    Computer-Aided Space Shuttle Orbiter Wing Design Study

    W. P. Phillips / J. P. Decker / T. R. Rau et al. | NTIS | 1974


    Aerodynamic heating of a space shuttle delta-wing orbiter

    Lockman, W. K. / Derose, C. E. | NTRS | 1971


    Aerodynamic Heating of a Space Shuttle delta-Wing Orbiter

    W. K. Lockman / C. E. Derose | NTIS | 1971


    Space Shuttle Orbiter Landing Loads Optimization

    Purtle, L. / Fann, C. / Eich, P. et al. | British Library Conference Proceedings | 1995