1. Fig. 1 above portrays an overall closed-loop architecture of autonomous relative navigation of a client satellite with an integrated sensor
System composed of the SIGI (space Integrated GPS/INS), a star tracker for gyro updates, an imaging sensor to determine azimuth-elevation
of the client satellite, and a co-boresighted laser range finder. For more details of the system, see Hablani, H.B., “Autonomos Inertial
Relative Navigation with Sight-Line-Stabilized Integrated Sensors for Spacecraft Rendezvous,” AIAA J. Guidance, Control, and Dynamics,
Vol. 32, No. 1, January-February 2009, pp

2. Fig. 7 illustrates the imaging of a client satellite with a sensor
on a chaser satellite, yielding azimuth and elevation angle
of the client satellite relative to the chaser satellite. For details,
see Hablani, 2009, op cit.
Fig. 5 portrays glide-slope guidance of the chaser satellite to
approach a target satellite, aided with relative navigation. For
Details, see Hablani, 2008, op cit., and Hablani, 2009, op cit.

3. Fig. 1 above depicts a single-axis closed-loop focal plane pointing and tracking system for relative navigation and guidance of a chaser satellite to get closer to a target satellite for rendezvous, inspection, or to repair it. For detailed functioning of this system, see Hablani, H.B., “Imaging Sensors Pointing and Tracking Controller Insensitive to Inertial Sensors Misalignments,” AIAA J. Guidance, Conrol, and Dynamics, Vol. 31, No. 4, July-August 2008, pp

4. The above figure shows that the line-of-sight command estimation error
is essentially the same as the star tracker misalignment about the
same axis. This biased command estimation error, however, does not
cause bias in the focal plane image of the target, as shown in the figure
below . For details, see Hablani, 2008, op cit.
True and estimated inertial rate commands about
the sensor focal plane y-axis: The rate commands
change discretely with each firing of thrusters
decreasing, in steps, relative velocity of the satellite
to rendezvous.