Year unknown•NASA STI Repository (National Aeronautics and Space Administration)Open access

Derivation of a general perturbation solution - Its application to determination of orbit

George H. Born

Abstract

Analytical solution to three-body problems is applied to the problem of predicting the orbit of a lunar satellite and determining the orbit of a near-earth satellite. Using this solution, the state vector may be generated at any time without intermediate numerical extrapolation.

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Available abstract

Key concepts: Extrapolation, Orbit determination, Perturbation (astronomy), Orbit (dynamics), Frozen orbit, Satellite, State vector, Ground track