An investigation of the error associated with the linear propagation was conducted and the corresponding MATLAB functions were written. This demonstration (LOP_Demo.m) propagates the space shuttle and the Hubble space telescope using both the Keplerian 2-body orbital propagation routine and the Clohessy-Wiltshire Hill linear propagation technique as described in Vallado. Error comparisons between linear propagation and non-linear propagation are computed.
This set of functions will allow the use of completely vectorized linear propagation in your MATLAB code projects. Included are the necessary routines to convert back and forth between Hill's reference frame and ECI coordinates. All solutions were validated against Vallado's MATLAB routines as well as his error chart (Pg. 415 of Fundamentals of Astrodynamics and Applications. Third Edition. 2007).
Removed unnecessary example function.
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