The use of simplified computational schemes for the estimation of the orbital parameters of spacecraft

Details The use of simplified computational schemes for the estimation of the orbital parameters of spacecraft The use of simplified computational schemes for the estimation of the orbital parameters of spacecraft

Nov 1975

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1975kosis..13..932c&link_type=abstract

Kosmicheskie Issledovaniia, vol. 13, Nov.-Dec. 1975, p. 932-935. In Russian.

Physics

Newton-Raphson Method, Orbit Calculation, Satellite Orbits, Convergence, Iterative Solution, Maximum Likelihood Estimates, Orbit Perturbation, Partial Differential Equations, Secular Variations

Scientific paper

The paper formulates conditions, in the framework of the Newton method, under which spacecraft orbital parameters can be estimated by means of calculation of partial derivatives. The maximum likelihood method is applied to the estimation of the parameters of a satellite orbiting the equatorial plane of a spheroid, taking into account secular perturbations.

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