Path: Orbit/OrbitCoord
% Transform to ECI frame from tangential coordinates. Since version 7. -------------------------------------------------------------------------- Form: m = MEQToECI( r, v ) -------------------------------------------------------------------------- ------ Inputs ------ r (3,1) Position (km) v (3,1) Velocity (km/s) ------- Outputs ------- m (3,3) Transformation matrix --------------------------------------------------------------------------
Math: Linear/Cross Math: Linear/Unit
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