Abstract
The Space Station Attitude Determination system (ADS) will utilize star trackers with CCD optical sensors and inertial sensor assemblies (ISA) with ring laser gyro (RLG) inertial rotation sensors. The ADS will manipulate star data from the star trackers--star position and magnitude--to autonomously initialize the space station attitude and to provide periodic updates to a Kalman filter during normal operation. This paper describes the functional interfacing between the star trackers and the Attitude Determination Function (ADF)--ADS central processor resident software--that provides for the exchange of data and commands between the star tracker and the ADF. This paper also describes the process whereby the data received from the star tracker is processed for generation of an initial attitude for delivery to the Kalman filter for an attitude update.© (1993) COPYRIGHT SPIE--The International Society for Optical Engineering. Downloading of the abstract is permitted for personal use only.
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