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CHANGELOG.md

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SatelliteToolboxPropagator.jl Changelog

Version 0.3.2

  • Feature The functions propagate, propagate!, propagate_to_epoch, and propagate_to_epoch! of Propagators can now receive a vector of instants and the propagation will happen in multiple threads, if possible. The number of tasks can be configured using the keyword ntasks. If ntasks = 1, the algorithm falls back to the single thread version, leading to no overhead.
  • Feature We added support for the objects defined in Dates in the propagation functions. propagate, propagate!, and step! can now receive an object of type Dates.Period or Dates.CompoundPeriod. On the other hand, propagate_to_epoch and propagate_to_epoch! now supports an epoch specified using DateTime.
  • Enhancement We implemented dedicate copy to all propagators defined here, leading to a substantial gain compared to the previous version that relies on deepcopy.
  • Enhancement We increase the number of precompiled function signatures.

Version 0.3.1

  • Enhancement Minor source-code updates.
  • Enhancement We reduced the allocations in all functions that fit mean elements.

Version 0.3.0

  • BREAKING We removed the possibility to add a mean motion time-derivative to J2 and J4 propagators. The theory we used to code those algorithms does not take into account such perturbations. Hence, the propagation accuracy would degrade very fast in those case with the mean motion perturbation.
  • BREAKING The symbol to indicate a time-derivative in the structures of the propagators was changed from δ to ∂.
  • BREAKING Enhancement We modified all the propagators to remove unnecessary variables in their structures after the redesign.
  • Enhancement We improved the J2 and J4 propagators given Kozai's theory.
  • Enhancement We updated the dependency compatibility bounds.

Version 0.2.1

  • Bugfix Fix the default constant name in the function twobody.

Version 0.2.0

  • BREAKING Bugfix The mean elements computed in the SGP4 API Propagators.mean_elements was returning a set of osculating elements. This behavior is now fixed since the function now updates the epoch of the initial TLE to the last propagation instant.
  • Feature Propagators API now have functions to fit mean elements.
  • Feature We added functions to fit and update mean elements in all supported propagator but the two-body orbit propagator.
  • Feature We added the osculating version of the J4 propagator, called J4 Osculation Orbit Propagator.
  • Info The minimum version for SatelliteToolboxSgp4.jl was increased to 2.1.

Version 0.1.0

  • Initial version.
    • This version was based on the code in SatelliteToolbox.jl.