A viable concept would utilize a spacecraft pair capable
of flying in a flexible formation. The main craft
would have a precision star-tracker and an accelerometer
and would be capable of precise navigation, with
disturbances, to a level less than _ 10−9 cm/s2 in the
low-frequency acceleration regime. Mounted on the
front would be a disk-shaped probe with laser cornercubes
embedded. Once the configuration is on its
solar system escape trajectory, will undergo no further
navigation maneuvers, and is at a heliocentric
distance of _ 5−20 AU, the co-rotating disk would be
released from the primary craft. (This concept is essentially
a version of a disturbance-compensation system
with a test mass being outside of the spacecraft.)
The probe will be passively laser-ranged from the primary
craft with the latter having enough delta-V to
maneuver with respect to the probe, if needed. The
distance from the Earth to the primary would be determined
with either standard radio-metric methods
operating at Ka-band or with optical communication.
Note that any dynamical noise at the primary would
be a common mode contribution to the Earth-primary
and primary-probe distances. This design satisfies the
primary objective, which would be accomplished by
the two-staged accurate navigation of the probe with
sensitivity down to the 10−10 cm/s2 level.