Autonomous satellite navigation by stellar refractionThis 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.
Document ID
19830060477
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Gounley, R. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena, CA; Charles Stark Draper Laboratories, Inc. Cambridge, MA, United States)
White, R. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Gai, E. (Charles Stark Draper Laboratories, Inc. Cambridge, MA, United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1983
Subject Category
Space Communications, Spacecraft Communications, Command And Tracking