Satellite Orbit Perturbations in Vector Form

Abstract

THE first-order perturbation theory of satellite orbits can be formulated simply and elegantly in terms of constants of the unperturbed motion using vector methods. For let the equation of motion be: where μ = GM (M = mass of the earth), and F is a general perturbing force (per unit mass). The energy E and angular momentum h (both per unit mass) defined as: are constants of the unperturbed motion. Hamilton's integral, which may be written in the form1: provides a further constant of the unperturbed motion under an inverse square law force. Taking scalar products with h and r, k is seen to be a vector of length μe lying along the major axis in the direction of apogee. The orbit is over-determined by E, h and k which give seven scalar equations.

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References

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    Milne, E. A., Vectorial Mechanics, 236 (Interscience Pub., New York, 1948).

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    King-Hele, D. G., Proc. Roy. Soc., A, 247, 49 (1958).

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    Herrick, S., Pub. Astron. Soc. Pacific, 60, 321 (1948).

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    Musen, P., J. Geophys. Res., 65, 1391 (1960).

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ALLAN, R. Satellite Orbit Perturbations in Vector Form. Nature 190, 615 (1961). https://doi.org/10.1038/190615a0

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