Application of the delta-rho perturbation method to autonomous orbit computation

Details Application of the delta-rho perturbation method to autonomous orbit computation Application of the delta-rho perturbation method to autonomous orbit computation

Aug 1984

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1984adans..54.1287s&link_type=abstract

IN: Astrodynamics 1983; Proceedings of the Conference, Lake Placid, NY, August 22-25, 1983. Part 2 (A84-30526 13-13). San Diego,

Astronomy and Astrophysics

Astronomy

Computerized Simulation, Error Analysis, Orbit Calculation, Orbit Perturbation, Satellite Orbits, Trajectory Analysis, Circular Orbits, Geosynchronous Orbits, Gravitational Effects, Harmonic Analysis, Numerical Integration, Position Errors, Velocity Errors

Scientific paper

Consideration is given to the possible application to a case in which the first orbit of an earth satellite, generated in a large ground-based computer, is taken as the reference orbit and the second, third, and later orbits are the dispersed orbits. It is found that the delta-rho method can be applied to orbits whose period is essentially that of the earth's rotation by increasing the time at points on the reference orbit by multiples of the orbital period. Also established is that truncating the earth's gravitational field after the J sub 2 term in the delta-rho equations leads to satisfactory results compared with the tenth-order model implemented in the generalized variation-of-parameters program. For the circular, equatorial, geosynchronous orbit, an integration step-size of one-fifth the orbital period produces no observable increase in the truncation error.

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