Spacecraft rendezvous and docking using measurements from satellite navigation equipment combined with the optical subsystem for final approach

The paper discusses an integrated system for spacecraft rendezvous and docking using measurements from satellite navigation equipment combined with the optical final approach subsystem (OFAS) which generates high-precision relative position vector during final approach. It addresses issues involved in designing an OFAS which has to operate in an environment exposed to sunlight and provides an estimate for the accuracy of the relative position measurements depending on the current range and OFAS configuration. Simulations have been run of the final approach involving simultaneous control from the satellite navigation equipment and OFAS. It was shown that at the moment of initial contact the approach accuracy of 2-5 cm for relative position, and of ~1 cm/s for velocity is achieved.