Piecewise acceleration orbital modeling: a GOCE satellite case study

Abstract In this work, the Precise Science Orbit (PSO) of Gravity Field and Steady-State Ocean Circulation Explorer Mission (GOCE) satellite, acquired via European Space Agency, served as reference orbit for testing various variants GOCE satellite modeling. The positions along reduced-dynamic PSO were treated pseudo-observations in improvement process least squares sense. This was realized using dedicated extended Toruń Processor software which enabled determining corrections to orbital initial conditions set parameters, necessary determine additional empirical accelerations radial-track, along-track cross-track directions. These piecewise determined successive equal intervals (pieces) into processed arcs divided. For modeling accelerations, polynomials different degrees used. obtained RMS differences between improved orbits arc lengths up 1-day. best fits 1-day range from 2.0 3.2 mm with significantly worst results direction. Based on solutions determined, number parameters adopted accuracy thresholds upper limit their number, that can be estimated depending length arc, under given numerical obtained. optimal form polynomial also depends partly arc. shorter (45 min less), second- third- fourth-order gives results, while longer (90, 180, 360, 720 1440 min), zero- first-degree are most effective. A very promising solution fit 0.1 a 1-min perspective future use short approach arcs. Additionally, non-equal numbers pieces radial-along-and directions case an 1-day, distribution residuals statistics aforementioned radial-, along-and presented.