This paper discusses three optical autocollimation systems for star simulat
ors, used in the functional monitoring systems of optoelectronic star senso
rs during ground testing and after the spacecraft is put into orbit. The la
youts used here differ in the design features of the objectives of the sens
ors, the position of the aperture stop, and the shape of the field. (C) 200
1 The Optical Society of America.