Accession Number:

AD0256666

Title:

EQUATIONS OF PERTURBED MOTION FOR A SATELLITE IN A NEARLY CIRCULAR, NEARLY EQUATORIAL ORBIT

Descriptive Note:

Corporate Author:

RAND CORP SANTA MONICA CALIF

Personal Author(s):

Report Date:

1961-02-27

Pagination or Media Count:

73.0

Abstract:

A set of differential equations is derived which defines the perturbed motion of a celestial body in terms of a particular set of orbital parameters. This set of orbital parameters is well suited to orbits that are circular or nearly so, since no singularities occur in the equations when the orbital eccentricity vanishes. In addition, this set of orbital parameters may be used to define orbits of small or zero inclination. The set of equations is given in the forms for both elliptic and circular orbits, with the perturbing acceleration expressed in terms of rectangular coordinates and derivatives of a disturbing function. Applications of the equations to the calculation of general perturbations, special perturbations, and orbit transfers are suggested. Author

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Distribution Statement:

APPROVED FOR PUBLIC RELEASE