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Aerospace blockset >> Blocks > KEPLERIAN_PROPAGATOR

KEPLERIAN_PROPAGATOR

This Xcos block allows for keplerian orbit propagation.

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Description

Block allows for propagation of Keplerian orbital elements from epoch time to the current time. As the model is Keplerian, only the mean anomaly varies. This block works for any type of orbit and any type of orbital elements. Event input activates the propagation. Classical Keplerian arguments (in order used in block input) are:

  • sma : semi-major axis [m]

  • ecc : eccentricity

  • inc : inclination [rad]

  • pom : periapsis argument [rad]

  • raan : right ascension of ascending node [rad]

  • anm : mean anomaly [m]

  • Data types

    Dialog box

    Currently there is no dialog box for this block.

    Default properties

    Currently there are no properties for this block.

    Interfacing function

    Computational function

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