Semianalytic integration of high-altitude orbits under lunisolar effects

DOI10.1155/2012/659396zbMath1264.70034OpenAlexW2041399174WikidataQ58911553 ScholiaQ58911553MaRDI QIDQ1955051

Yanyan Li

Publication date: 11 June 2013

Published in: Mathematical Problems in Engineering (Search for Journal in Brave)

Full work available at URL: https://doi.org/10.1155/2012/659396

Mathematics Subject Classification ID

Celestial mechanics (70F15) Orbital mechanics (70M20)

Uses Software

• RODAS
• MathATESAT
• Astrodynamics

Cites Work

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• Third-body perturbation in the case of elliptic orbits for the disturbing body
• Controlling the eccentricity of polar lunar orbits with low-thrust propulsion
• Some initial conditions for disposed satellites of the systems GPS and Galileo constellations
• Higher-order analytical attitude propagation of an oblate rigid body under gravity-gradient torque
• Fundamentals of astrodynamics and applications. With technical contributions by Wayne D. McClain.
• Solving Ordinary Differential Equations I
• Lunar perturbations of artificial satellites of the earth
• Canonical transformations depending on a small parameter
• The main problem of artificial satellite theory for small and moderate eccentricities
• Equivalence of the perturbation theories of Hori and Deprit
• Delaunay normalisations

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