The motion of artificial satellites in the set of Eulerian redundant parameters

Statistics – Computation

Scientific paper

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Astrodynamics, Orbit Calculation, Satellite Orbits, Satellite Perturbation, Algorithms, Angular Velocity, Boundary Value Problems, Earth Gravitation, Euler Equations Of Motion, Rigid Structures

Scientific paper

The connections between orbit dynamics and rigid-body dynamics are established throughout the Eulerian redundant parameters, and the perturbation equations for any conic motion of artificial satellites are derived in terms of these parameters. A general recursive and stable computational algorithm is also established for the initial-value problem of the Eulerian parameters for satellites prediction in the earth's gravitational field with axial symmetry. Applications of the algorithm are considered for the two cases of short- and long-term predictions. For the short-term prediction, the problem of the final state prediction is considered of some typical ballistic missiles in the geopotential model with zonal harmonic terms up to J(36), while for the long-term prediction, the perturbed J(2) motion of Explorer 28 over 100 revolutions is considered.

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