1. A method for determining the position of a spacecraft based upon a determination of direction vectors and spin vectors, in which sensor data and spin data are determined as input variables for position determination, said method comprising: a sensor measuring a first unit vector as a direction vector, in a body-fixed coordinate system; computing a second unit vector as a reference direction vector in a reference coordinate system, based on the path position of the spacecraft and an orbit model; computing an overall spin vector of the spacecraft in the body-fixed coordinate system, as a third vector determination; computing a reference overall spin vector of the spacecraft in the reference coordinate system by time propagation of known initial values of the overall spin of the spacecraft, as a fourth vector; and determining the position of the spacecraft based on said first through fourth vectors.