Star Identification

Background

An in-space star-pattern identification capability is becoming an increasingly important aspect of spacecraft navigation. It has been specified as an attitude system requirement for several forthcoming missions, including Proteus, Rosetta and Cassini. The ability to recognise stars autonomously and to determine spacecraft attitude greatly enhances the value of star-camera data and has many advantages. Spacecraft designed with this inherent autonomy are less reliant on expensive and fragile ground communication links, are more robust against system failure, require fewer sensors and have higher pointing-accuracy capabilities. Autonomous star-pattern identification may be of particular benefit to deep-space missions where communication delays make interactive decision-making inefficient and time consuming, contributing to a significant portion of the overall mission cost.

Despite these advantages, few commercially available star-camera systems with an autonomous star-identification capability have been developed to date. The techniques and methods of those few systems in existence are highly experimental, and the development of reliable identification strategies is an active area for research.

Research into Rapid Autonomous Star-Identification Techniques

I have worked to develop a new star-identification strategy capable of identifying stars in a single camera image with minimal processing. The system attempts to identify groups of stars by comparing their features to those in a pre-stored catalogue. Although this general approach is not new, particular methods of processing raw star-camera data, of choosing star groups and features and of encoding the catalogue, provide new and innovative advances in autonomous star recognition. These new approaches offer significant performance advantages over existing technologies.

My research includes work on fast, non-sequential search techniques. The algorithm dramatically reduces the number of comparisons required to make an identification by implementing a divide-and-conquer strategy based on a binary tree search technique. With knowledge of star-camera observation accuracies, a search algorithm can be constructed so that the correct star will always be identified, if not uniquely, then to within a small set of possibilities (assuming that the features are correctly identified). Not only does this approach offer the possibility of real-time star identification, it also expands the range of star-cameras suitable for adaptation to autonomous attitude determination to include high-accuracy, narrow field-of-view star cameras. Previously, the size of the required reference catalogues has made star identification from narrow fields of view impractical. The new non-sequential search strategy allows identification matches to be made from catalogues of 50000 stars or more in minimal time with low storage requirements.

Figure 1 shows a star-identification example. A CCD camera image of the sky is shown, overlaid with triads of stars identified by the system. The star-identification technique dramatically enhances the value of the star-location data generated by the camera, for attitude determination.

Figure 1: Star Identification of Triads of Stars From Star-Camera Frames.

An autonomous star identification processing system that exploits these aspects of my research is currently being developed by Matra Marconi Space U.K., in conjunction with star camera head manufacturers. Further information describing this research can be found here.

Links to Other Star Identification Sites

There are a number of web sites describing autonomous star identification systems. Most other techniques use separation features to make matches and use two modes: a slow initial identification mode and a faster track stars mode. These include in no particular order:

The MMS/SIRA AST20 has a 19 by 14 degree field of view. The electronics and optics weight 2.4 Kg and are packaged separately. The device identifies stars to magnitude 6.2 and has an update rate of 5 Hz (Hardware flown on Ariane 502).
The Ball CT633 has a field of view of 20 by 20 degrees. The electronics and optics combined unit has a mass of 5.5lbs. Time for initial acquisition is not reported. It is designed to track 5 stars at 5 Hz (no maximum rate specified). It uses a catalogue of 2000 stars and is sensitive down to magnitude +4.5. (Hardware flown on NEAR, February 1996, without autonomous identification software module).
The Ørsted Star Imager Group. Their system uses a 588 pixels by 752 pixels CCD and has a field of view of 16 by 22 degrees (1 pixel spans approximately 100" by 100"). The optics consists of a seven element lens with a 16mm focal length (f/0.69) and a point spread function diameter of 50 microns over the entire field of view. Total mass of the optics is 170g and has a power consumption of 0.5W. Their processing box employs a 50MHz Intel 80486 with OPTI 495slc/206 support chipset with 4MB DRAM. Total mass of processor board and box is 1.6kg and it consumes 4.0W. Time for initial acquisition is not reported but the system will track at 1 Hz (no maximum rate specified). It uses a catalogue of 11000 stars (2200 principle stars) and 2.2 million separations. (Due for launch August 1998).
The QUAST, Quasi Autonomous Star Tracker. This device will identify stars given a prior knowledge of its attitude (to a 4 degree accuracy). It has been approved for 5 flights.
The LLNL Star Tracker Stellar Compass. The camera has a wide 28.9 x 43.4-degree field of view. The system uses a RISC-3000 processor to identify stars down to magnitude 4.5 are measured. (Flown on Clementine, early 1994).
The CRI-15AS Autonomous Star Tracker. The camera has a 22 degree field of view. The optics and electronics weigh 0.4Kg and 1.6Kg respectively and consumes 8W of power. The system tracks typically 65 stars with a selectable rate of 2 Hz to 10 Hz (No maximum rate specified). Initial acquisition time is not reported.
The CAL CALTRAC Autonomous Star sensor. The camera has a 36 by 27 degree field of view and is specified to be sensitive down to magnitude +7.0 in a stare mode. The initial acquisition time is quoted as less than 100ms with a subsequent tracking rate of up to 100 Hz. The device has a mass of 2.75Kg and consumes up to 9W of power.
 

 

(c) Space Engineering Laboratory, 2014