Method of calculating lunisolar perturbances in AES intermediate orbit elements.

Details Method of calculating lunisolar perturbances in AES intermediate orbit elements. Method of calculating lunisolar perturbances in AES intermediate orbit elements.

Aug 1997

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1997kosis..35..378k&link_type=abstract

Kosmicheskie Issledovaniia, Tom 35, No. 4, p. 378 - 386

Computer Science

Artificial Satellites: Motions, Artificial Satellites: Perturbations

Scientific paper

A method for calculating lunisolar perturbations in the motion of artificial Earth satellites (AES) is proposed. The method is based on a representation of perturbations in the AES intermediate orbit elements as short truncated trigonometric series in multiples to a mean anomaly with coefficients being the functions of time, which are expanded into series in Chebyshev polynomials over 4-day intervals. Such a form of perturbations essentially saves both calculation time and computer memory.

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