Satellitetoolbox Propagators

SatelliteToolboxPropagators.jl

Unified API for analytical orbit propagators. Repo: JuliaSpace/SatelliteToolboxPropagators.jl

Available Propagators

Initialize and Propagate

# Init from KeplerianElements or orbital parameters
orbp = Propagators.init(Val(:J2), orb)
orbp = Propagators.init(Val(:J2), epoch_jd, a, e, i, Ω, ω, f)

# Init from TLE (SGP4 only)
orbp = Propagators.init(Val(:SGP4), tle)

# Propagate by Δt seconds from epoch
(r_i, v_i) = Propagators.propagate!(orbp, Δt)

# Propagate to a specific epoch
(r_i, v_i) = Propagators.propagate_to_epoch!(orbp, jd)

# Step from current time (not epoch)
(r_i, v_i) = Propagators.step!(orbp, Δt)

# One-shot: init + propagate
(r_i, v_i, orbp) = Propagators.propagate(Val(:J2), Δt, epoch_jd, a, e, i, Ω, ω, f)

Return as OrbitStateVector

sv = Propagators.propagate!(orbp, Δt, OrbitStateVector)

Vectorized Propagation

(vr, vv) = Propagators.propagate!(orbp, [0.0, 60.0, 120.0]; ntasks=4)

Fitting Mean Elements

mean_elements = Propagators.fit_mean_elements(Val(:J2), vjd, vr_i, vv_i)

Query Propagator State

Propagators.epoch(orbp)            # Epoch [JD]
Propagators.last_instant(orbp)     # Last propagation time [s]
Propagators.mean_elements(orbp)    # Current mean elements
Propagators.name(orbp)             # Propagator name string

Key Conventions

• Units: meters, m/s, seconds for Δt, Julian Day for epochs
• Propagator selection via Val(:Symbol) dispatch
• Dates.Period inputs auto-converted to seconds
• Output frame: inertial (ECI) for analytical propagators, TEME for SGP4
• Re-exports SatelliteToolboxBase and SatelliteToolboxSgp4