Position information is a fundamental aspect of spacecraft, playing a crucial role in user orbit maintenance, formation flight, configuration maintenance, and business operations. User positions can be predicted from orbital parameters or directly measured and calculated; similarly, continuous positioning can also obtain user orbits. Orbit determination methods can be divided into ground-based, space-based, and astronomical orbit determination based on the location of the ranging signal source. Ground-based orbit determination mainly includes space telemetry and control (such as USB, unified S-band telemetry and control), Satellite Laser Ranging (SLR), Doppler Orbitography and Radiopositioning Integrated by Satellite (DORIS), and Very Long Baseline Interferometry (VLBI); space-based orbit determination mainly includes Global Navigation Satellite Systems (GNSS) and Tracking and Data Relay Satellite Systems (TDRSS); astronomical orbit determination mainly includes satellite sensors and pulsars. Although there are many orbit determination methods, each has its advantages and disadvantages and cannot effectively solve the positioning problem of spacecraft, especially for medium and high orbit spacecraft. Medium and high orbit spacecraft have high orbital altitudes, and the ground observation angle is limited, with orbit determination accuracy at the hundred-meter level: for example, for a navigation satellite with an orbital altitude of 22,000 km, the angle from the satellite to the tangent of the Earth's edge is less than 26°; the tangent angle of the geosynchronous orbit satellite is even less than 18°. In actual station layout, due to political factors and terrain restrictions, it is impossible to set up stations globally and achieve full-arc coverage. Space-based positioning, which raises the reference position and is not restricted by region, has become the ideal positioning method for medium and high orbit spacecraft. The space-based navigation system represented by the GPS system is widely used in low-orbit satellite orbit determination, but its main lobe only covers 4.5% of GEO/HEO orbit users, and even with the addition of navigation signal sidelobes, the quadruple coverage is less than 30%. The Tracking and Data Relay System is mainly used for orbit determination of medium and low orbit, with a theoretical accuracy of up to 20 m, but it cannot be used for GEO/HEO satellite orbit determination.