A concurrent engineering approach to the design and analysis of a space-borne Electro-Optical (EO) sensor is presented.
A detailed design of an infrared telescope payload is developed by an interdisciplinary team of mechanical, structural,
thermal, and optical engineers using a Simulation Driven Engineering (SDE) software environment. The telescope
payload design is also integrated with a conceptual level design of the space segment of a mission that incorporates the
payload. The flow of the concurrent design process is described, and design outputs are provided.
The Aerospace Corporation has developed a testbed for studying pointing, acquisition, and tracking systems for
lasercom terminals. The testbed consists of two configurable terminals that are currently set up to represent a GEO-to-
GEO link. Each terminal has the ability to point open-loop, execute scan patterns, and track a received beam. The system
operates in small-beam space and consists of a far-field space simulator and two lasercom terminals operating at 473 nm
and 633 nm with representative hardware (fast steering mirrors, optical detectors, etc.). This paper discusses the software
developed for the testbed and the characterization of its performance, which includes open-loop pointing accuracy and
residual tracking error in the presence of applied disturbances. Analytical predictions are compared to experimental
results. Each terminal has the ability to progress from acquisition to tracking mode and the two terminals together
demonstrate the cooperative acquisition process.