Nonsingular elements in description of the motion of small eccentricity and inclination satellites

Details Nonsingular elements in description of the motion of small eccentricity and inclination satellites Nonsingular elements in description of the motion of small eccentricity and inclination satellites

Feb 1986

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1986cemec..38..101w&link_type=abstract

Celestial Mechanics (ISSN 0008-8714), vol. 38, Feb. 1986, p. 101-109.

Statistics

Computation

8

Astrodynamics, Eccentricity, Orbit Calculation, Satellite Orbits, Equations Of Motion, Euler-Lagrange Equation, Orbital Elements

Scientific paper

A nonsingular-element formulation of the Lagrange equations of motion for satellites with low-inclination low-eccentricity orbits is derived. The inclination and eccentricity functions proposed by Nacozy and Dallas (1977) and their derivatives are corrected, and the final forms obtained are shown to be at least as accurate as the less complicated conventional functions of Kaula (1966). Numerical computations for a satellite with a = 1.1 earth radii, e = 0. 0001, i = 0.5 deg, omega = Omega = 50 deg, and M = 0.505 r give a position difference after 24 h of the order of 1 mm when the eccentricity function is limited to q = + or - 3.

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