This paper describes the techniques involved in determining the aerodynamic stability derivatives for the frequency domain analysis of the Space Launch System (SLS) vehicle. Generally for launch vehicles, determination of the derivatives is fairly straightforward since the aerodynamic data is usually linear through a moderate range of angle of attack. However, if the wind tunnel data lacks proper corrections then nonlinearities and asymmetric behavior may appear in the aerodynamic database coefficients. In this case, computing the derivatives becomes a non-trivial task. Errors in computing the nominal derivatives could lead to improper interpretation regarding the natural stability of the system and tuning of the controller parameters, which would impact both stability and performance. The aerodynamic derivatives are also provided at off nominal operating conditions used for dispersed frequency domain Monte Carlo analysis. Finally, results are shown to illustrate that the effects of aerodynamic cross axis coupling can be neglected for the SLS configuration studied


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    Title :

    Estimation of Aerodynamic Stability Derivatives for Space Launch System and Impact on Stability Margins


    Contributors:
    Pei, Jing (author) / Wall, John (author)

    Conference:

    AIAA Atmospheric Flight Mechanics Conference ; 2013 ; Boston, MA, United States
    AIAA Guidance, Navigation, and Control Conference ; 2013 ; Boston, MA, United States


    Publication date :

    2013-08-19


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English





    Estimation of Aerodynamic Stability Derivatives for Space Launch System and Impact on Stability Margins (AIAA 2013-4684)

    Pei, J. / Wall, J. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2013



    Aerodynamic stability characteristics of the Apollo launch escape vehicle

    Hondros, J. G. / Moseley, W. C., Jr. | NTRS | 1967


    Aerodynamic stability characteristics of the Apollo launch escape vehicle

    Moseley, William C. / Hondros, James G. | TIBKAT | 1967