Publication Date:
2019-07-13
Description:
This paper describes an error analysis of an autonomous navigator using refraction measurements of starlight passing through the upper atmosphere. The analysis is based on a discrete linear Kalman filter. The filter generated steady-state values of navigator performance for a variety of test cases. Results of these simulations show that in low-earth orbit position-error standard deviations of less than 0.100 km may be obtained using only 40 star sightings per orbit.
Keywords:
SPACE COMMUNICATIONS, SPACECRAFT COMMUNICATIONS, COMMAND AND TRACKING
Type:
AIAA PAPER 83-2211
,
Guidance and Control Conference; Aug 15, 1983 - Aug 17, 1983; Gatlinburg, TN
Format:
text
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