Modified Equinoctial Elements

Author: Tianjiang Shuo

Website: https://cislunarspace.cn

Definition

A non-singular set of orbital elements for low-thrust trajectory optimization, consisting of the semilatus rectum P, eccentricity vector components (ex, ey), inclination vector components (hx, hy), and true longitude L. Compared to classical Keplerian elements, MEEs are singularity-free for circular orbits (zero eccentricity) and equatorial orbits (zero inclination), and their transformation to Cartesian coordinates is smooth, making them superior for co-state equation derivation in optimal control.

Application Value

This term has significant practical applications in cislunar mission planning and execution.

  • Hidden-Genes Genetic Algorithm, HGGA
  • Variable-Size Design Space, VSDS
  • Station-Keeping
  • Target Point Method

References

  • Singh et al., 2021
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Contributors: ouyangjiahong, Ou Yang Jiahong