  We develop an integrated guidance and control system that in conjunction with
a stabilized seeker and landing site detection software can achieve precise and
safe planetary landing. The seeker tracks the designated landing site by
adjusting seeker elevation and azimuth angles to center the designated landing
site in the sensor field of view. The seeker angles, closing speed, and range
to the designated landing site are used to formulate a velocity field that is
used by the guidance and control system to achieve a safe landing at the
designated landing site. The guidance and control system maps this velocity
field, attitude, and rotational velocity directly to a commanded thrust vector
for the lander's four engines. The guidance and control system is implemented
as a policy optimized using reinforcement meta learning. We demonstrate that
the guidance and control system is compatible with multiple diverts during the
powered descent phase, and is robust to seeker lag, actuator lag and
degradation, and center of mass variation induced by fuel consumption. We
outline several concepts of operations, including an approach using a preplaced
landing beacon.
