Differential equations for the nonangular elements of a hyperbolic orbit

Details Differential equations for the nonangular elements of a hyperbolic orbit Differential equations for the nonangular elements of a hyperbolic orbit

Apr 1977

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1977mvsfa..18...34c&link_type=abstract

Moskovskii Universitet, Vestnik, Seriia III - Fizika, Astronomiia, vol. 18, Mar.-Apr. 1977, p. 34-42. In Russian.

Mathematics

Astrodynamics, Celestial Mechanics, Hyperbolic Trajectories, Orbital Elements, Planetary Gravitation, Differential Equations, Eccentric Orbits, Orbit Calculation, Series (Mathematics), Trigonometry

Scientific paper

Differential equations are derived for the semimajor axis, eccentricity, and the sine of the angle of inclination (nonangular elements) of a hyperbolic intermediate orbit of a mass point that moves in the gravitational field of an oblate planet subjected to disturbances by another planet. The intermediate orbit is deduced from a symmetric version of the problem of two fixed centers, using the Hill term in the expansion of the perturbing planet's potential as the perturbing function, and taking the ellipticity of the planet's motion into consideration. The right-hand sides of the equations derived are written in the form of trigonometric series.

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