Normal form stability estimates are a basic tool of Celestial Mechanics for characterizing the long-term stability of the orbits of natural and artificial bodies. Using high-order normal form constructions, we provide three different estimates for the orbital stability of point-mass satellites orbiting around the Earth. (i) We demonstrate the long-term stability of the semimajor axis within the framework of the J_2 problem, by a normal form construction eliminating the fast angle in the corresponding Hamiltonian and obtaining {mathcal {H}}_{J_2}. (ii) We demonstrate the stability of the eccentricity and inclination in a secular Hamiltonian model including lunisolar perturbations (the ‘geolunisolar’ Hamiltonian {mathcal {H}}_mathrm{gls}), after a suitable reduction of the Hamiltonian to the Laplace plane. (iii) We numerically examine the convexity and steepness properties of the integrable part of the secular Hamiltonian in both the {mathcal {H}}_{J_2} and {mathcal {H}}_mathrm{gls} models, which reflect necessary conditions for the holding of Nekhoroshev’s theorem on the exponential stability of the orbits. We find that the {mathcal {H}}_{J_2} model is non-convex, but satisfies a ‘three-jet’ condition, while the {mathcal {H}}_mathrm{gls} model restores quasi-convexity by adding lunisolar terms in the Hamiltonian’s integrable part.
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