In theoretical dynamics, missile motion is described in six degrees of freedom. The corresponding system of equations of motion contains external forces lift, drag and side force besides motor thrust and gravity, and as external moments the moments of pitch, yaw and roll. Forces and moments - which are dependent on flight conditions such as angles of attack, yaw, and roll, flight speed, acceleration and the angular velocities of pitch, yaw and roll - may be given as partial derivatives of these variables. The connection between aerodynamic modelling and the equation of motions is explained. Simple missile motions are chosen to explain steady and dynamic stability. The influence of steady and dynamic (quasisteady) derivatives is estimated. From literature, examples for the simulation of complicated flight motions caused by non-linear unsteady forces and moments are selected and shown in diagrams.


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    Titel :

    Application to Missile Dynamics


    Beteiligte:

    Erscheinungsdatum :

    1980


    Format / Umfang :

    16 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Application to missile dynamics

    Schneider, C.P. | TIBKAT | 1980


    Overall Missile Dynamics

    Runyon, H. L. | NTRS | 1962


    Prediction of Tactical Missile Dynamics

    L. E. Ericsson | NTIS | 1989


    Rolleron dynamics in missile applications

    Taur, Der-Ren / Chern, Jeng-Shing | AIAA | 1999


    Agile Missile Dynamics and Control

    Wise, K.A. | Online Contents | 1998