An analytical method for determining the elements of Keplerian orbits according to two positions of the spacecraft

Details An analytical method for determining the elements of Keplerian orbits according to two positions of the spacecraft An analytical method for determining the elements of Keplerian orbits according to two positions of the spacecraft

Nov 1989

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1989kosis..27..803s&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 27, Nov.-Dec. 1989, p. 803-807. In Russian.

Astronomy and Astrophysics

Astronomy

Astrodynamics, Elliptical Orbits, Orbit Calculation, Orbital Position Estimation, Spacecraft Motion, Analytic Functions, Differential Equations, Eccentricity, Roots Of Equations

Scientific paper

An analytical method is presented which makes it possible to determine Keplerian orbital elements according to two positions of the spacecraft without the use of an iteration process. The method is suitable for determining the elements of orbits with low eccentricity (e not greater than 0.04) for angular distances between the two radius-vectors not exceeding 90 deg. Calculation errors and calculation length are evaluated, and numerical results are presented.

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