This invention discloses a method,
system, and product for estimating the arm length of a Taiji mission considering
satellite relative motion compensation. The method includes: reading
ephemeris data of key gravitational bodies during the
simulation period, establishing the orbital dynamics equations of the
satellite formation, solving the equations using a high-precision numerical
integration algorithm, and outputting
satellite orbit simulation data; generating basic measurements including
noise and satellite-to-solar measurements based on the
satellite orbit simulation data, and correcting the inter-satellite distance measurements in the basic measurements by optical
signal propagation time to achieve satellite
relative motion compensation and outputting high-precision
observation data; receiving the high-precision
observation data, combining it with the orbital dynamics equations of the satellite formation, recursively updating and optimizing the state variables of the satellite formation based on a
Kalman filter algorithm, and outputting a high-precision estimate of the inter-satellite arm length; and visualizing the estimated satellite arm length and its error. This invention significantly improves the autonomy and reliability of space
gravitational wave detection missions.