JuliaSpace/SatelliteToolboxBase.jl: v2.0.0

Résumé fourni par la source

SatelliteToolboxBase v2.0.0 Diff since v1.2.0 Breaking Change: Add the type parameter Tanomaly to KeplerianElements, which now is KeplerianElements{Tanomaly, Tepoch, T}, to select the anomaly stored in the object (TrueAnomaly, EccentricAnomaly, or MeanAnomaly). Update the code that refers to KeplerianElements{Tepoch, T}. Breaking Change: Rename the fields of KeplerianElements to epoch, semi_major_axis, eccentricity, inclination, raan, argument_of_periapsis, and anomaly. Keep the old names (t, a, e, i, Ω, ω, and f) as property aliases, where f always returns the true anomaly. Breaking Change: Rename the field t of OrbitStateVector to epoch. Keep the old name as a property alias. Breaking Change: Promote the inputs of OrbitStateVector to float when obtaining the element type, as KeplerianElements already does. Hence, integer inputs no longer create an OrbitStateVector with integer elements. Breaking Change: Throw DimensionMismatch instead of ErrorException in rv_to_kepler when the input vectors do not have three elements. Breaking Change: Delegate is_leap_year to Dates.isleapyear, which no longer throws for negative years. Breaking Change: Throw ArgumentError in mean_to_eccentric_anomaly and mean_to_true_anomaly when max_iterations is lower than 1, instead of silently resetting it to 10. Support the true, eccentric, or mean anomaly in KeplerianElements, selected by the new type parameter Tanomaly. Use the constructor KeplerianElements{Tanomaly}(...) to create an object with the desired anomaly. The default remains the true anomaly. Add the getters true_anomaly, eccentric_anomaly, and mean_anomaly, which return the desired anomaly of a KeplerianElements object, converting it if necessary. Pass the keywords of the Newton-Raphson solver (tol and max_iterations) to those functions when the conversion starts from the mean anomaly. Add the orbit representation EquinoctialElements. Add the orbit representation AlternateEquinoctialElements instead of tan(i / 2)in the elementspandq`, keepingthem bounded and finite for every inclination, including retrograde equatorial orbits. Support all the conversions between KeplerianElements (wtialElements, AlternateEquinoctialElements, andOrbitStateVector in the Julia built-in conversion system (convert`). Add the abstract type AbstractEquinoctialElements, supertsandAlternateEquinoctialElements`, to dispatch on eitherequinoctial set. Use StyledStrings.jl instead of Crayons.jl for the methods. Crayons.jl is no longer a dependency. Remove the unused dependency Printf.jl. Scale the default tolerance of the Newton-Raphson solver ily` by the magnitude of the mean anomaly, avoiding iterationsthat cannot improve the solution. Compute the conversions between different orbit representaric type of the input and the target, so no precision is lostwhen converting to a wider type. Print the acceleration in the rich representation of `Orbiame layout as the other orbit representations. Fix the docstrings of EGM_1996_J3 and EGM_1996_J4, which named the EGM-2008 model, and add the references of the EGM constants. Add the .JuliaFormatter.toml configuration and format thhe coding style. Merged pull requests: :construction_worker: Add dependabot configuration file (#7) (@Copilot) :construction_worker: Bump the github-actions group with 2 updates (#8) (@dependabot[bot]) :construction_worker: Bump codecov/codecov-action from 5 to 6 in the github-actions group (#9) (@dependabot[bot]) :construction_worker: Bump julia-actions/setup-julia from 2 to 3 in the github-actions group (#10) (@dependabot[bot]) :construction_worker: Bump codecov/codecov-action from 6 to 7 in the github-actions group (#11) (@dependabot[bot]) :construction_worker: Bump actions/checkout from 6 to 7 in the github-actions group (#12) (@dependabot[bot]) ✨ Add mu keyword to rv/sv conversions (#13) (@fnawratil)

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