R. G. Brown and L. L. Hagerman

Peer Reviewed

Abstract: IT IS OBVIOUS that position fises obtained from the Navy Navigation Satellite System may be used t,o reset a pure inertial system on long missions where some form of resetting is desirable. This paper discusses a method of system integration whereby the doppler data is treated directly as the observable in a Kalman-filter reset scheme, and thus the intermediate step of computing a position fix is omitted. In the process, this method properly accounts for the vehicle velocity in any dynamical situation, which is a difficult problem when viewed from other approaches. Simulated computer results are presented.
Published in: NAVIGATION: Journal of the Institute of Navigation, Volume 16, Number 3
Pages: 260 - 270
Cite this article: Brown, R. G., Hagerman, L. L., "AN OPTIMUM INERTIAL DOPPLER-SATELLITE NAVIGATION SYSTEM", NAVIGATION: Journal of The Institute of Navigation, Vol. 16, No. 3, Fall 1969, pp. 260-270.
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