This Xcos block performs Earth Centered Inertial (ECI) to Earth Centered Earth Fixed (ECI) reference frame vector transformation.
This Xcos block performs Earth Centered Inertial (ECI) to Earth Centered Earth Fixed (ECI) reference frame vector transformation. Although the block allows to transform velocity as well as position velocity input can be ignored if unnecessary. Position input is mandatory, even when only velocity output is used. Third input with current simulation time in "modified julian day since 1950" needs to be always connected.
Input 1 (mandatory): 3x1 double (position in ECI reference frame)
Input 2 (optional): 3x1 double (velocity in ECI reference frame)
Input 3 (mandatory): 1x1 double (time in "modified julian day since 1950" format)
Output 1: 3x1 double (position in terrestial reference frame)
Output 2: 3x1 double (velocity in terrestial reference frame)
This block has no dialog box.
This block has no cofigurable properties.
macros/ECI_TO_ECF.sci
macros/AB_fr_convert.sci
CelestLab - CelestLab aerospace library
CL_fr_convert - CelestLab function used to perform the conversion from Earth Centered Inertial (ECI) to Earth Centered Earth Fixed (ECI) reference frame.
KEP_TO_CAR - Aerospace Blockset block allowing for conversion from classical keplerian orbital elements to position and velocity for an elliptic, hyperbolic or parabolic orbit
CJD_TIME - Aerospace Blockset block providing configurable way of feeding time to the simulation in "modified julian day since 1950" format.
PLOT_GROUNDTRACK - Aerospace Blockset block allowing to plot ground track of satellites orbiting Earth based on their position in terrestial reference frame.