Agent skill
satellitetoolbox-base
SatelliteToolboxBase.jl providing foundational types, constants, and orbit representations for the JuliaSpace ecosystem. Use when working with KeplerianElements, OrbitStateVector, anomaly conversions, Julian Date utilities, or SatelliteToolbox constants.
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SKILL.md
SatelliteToolboxBase.jl
Foundation package for the JuliaSpace SatelliteToolbox ecosystem. Repo: JuliaSpace/SatelliteToolboxBase.jl
CRITICAL: Unit Convention
SatelliteToolbox uses meters and m/s throughout. HAMMERHEAD libraries use km and km/s. Always convert at interop boundaries (* 1e3 or / 1e3).
Key Types
KeplerianElements{Tepoch, T} # t [JD], a [m], e, i [rad], Ω [rad], ω [rad], f [rad]
OrbitStateVector{Tepoch, T} # t [JD], r::SVector{3,T} [m], v::SVector{3,T} [m/s]
Ellipsoid{T} # a (semi-major), f (flattening) -> auto-computes b, e², el²
Constants
| Constant | Value | Unit |
|---|---|---|
GM_EARTH |
3.986004415e14 | m³/s² |
EARTH_EQUATORIAL_RADIUS |
6378137.0 | m |
EARTH_ANGULAR_SPEED |
7.292115e-5 | rad/s |
ASTRONOMICAL_UNIT |
1.496e11 | m |
SUN_RADIUS |
6.96342e8 | m |
JD_J2000 |
2451545.0 | Julian Day |
WGS84_ELLIPSOID |
Ellipsoid{Float64} | WGS-84 |
Orbit Conversions
kepler_to_rv(orb) # -> (r::SVector{3}, v::SVector{3}) in meters, m/s
kepler_to_sv(orb) # -> OrbitStateVector
rv_to_kepler(t, r, v) # -> KeplerianElements
sv_to_kepler(sv) # -> KeplerianElements
Anomaly Conversions (all radians, returns [0, 2π])
mean_to_eccentric_anomaly(e, M; max_iterations=10, tol=nothing)
mean_to_true_anomaly(e, M)
eccentric_to_true_anomaly(e, E)
true_to_eccentric_anomaly(e, f)
true_to_mean_anomaly(e, f)
Time Utilities
date_to_jd(year, month, day, hour, min, sec) # -> Julian Day
jd_to_date(JD) # -> (year, month, day, hour, min, sec)
jd_to_gmst(JD) # -> GMST [rad]
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