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This paper discusses a particular set of mathematical transformations that render the nonlinear problem of orbital mechanics into a linear problem. The linear ordinary differential equation then admits an analytical solution. While other approaches necessitate the evaluation of transcendental functions, this solution can be implemented using only the exponential function.

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This page is a summary of: Regular Celestial Mechanics and the Matrix Exponential, Journal of Guidance Control and Dynamics, November 2020, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/1.g005237.
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