Semianalytical method of satellite orbit computation

Details Semianalytical method of satellite orbit computation Semianalytical method of satellite orbit computation

Jun 1978

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1978acasn..19...18y&link_type=abstract

Acta Astronomica Sinica, vol. 19, June 1978, p. 18-23. In Chinese, with abstract in English.

Astronomy and Astrophysics

Astronomy

Numerical Integration, Orbit Calculation, Orbit Perturbation, Periodic Variations, Satellite Orbits, Secular Variations, Extrapolation, Long Term Effects, Orbital Mechanics, Perturbation Theory, Position Errors, Runge-Kutta Method

Scientific paper

Artificial satellite orbit calculation is classically analyzed in terms of short-period, long-period, and secular-variation components. While the classical analytical method is sufficiently accurate for the calculation of the short-period perturbation, this paper emphasizes the numerical integration method for computing long-period and secular-variation components. The accuracy achieved by linear extrapolation, the Euler method, and the Runge-Kutta method is discussed.

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