Agent skill
satellitetoolbox-propagators
SatelliteToolboxPropagators.jl providing a unified API for analytical orbit propagators (TwoBody, J2, J4, SGP4). Use when propagating orbits with analytical models, fitting mean elements, or comparing propagator outputs.
Install this agent skill to your Project
npx add-skill https://github.com/majiayu000/claude-skill-registry/tree/main/skills/other/other/satellitetoolbox-propagators
SKILL.md
SatelliteToolboxPropagators.jl
Unified API for analytical orbit propagators. Repo: JuliaSpace/SatelliteToolboxPropagators.jl
Available Propagators
| Symbol | Type | Description |
|---|---|---|
:TwoBody |
OrbitPropagatorTwoBody |
Keplerian two-body |
:J2 |
OrbitPropagatorJ2 |
J2 mean elements |
:J2osc |
OrbitPropagatorJ2Osculating |
J2 with osculating output |
:J4 |
OrbitPropagatorJ4 |
J4 mean elements |
:J4osc |
OrbitPropagatorJ4Osculating |
J4 with osculating output |
:SGP4 |
OrbitPropagatorSgp4 |
SGP4/SDP4 from TLE |
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.Periodinputs auto-converted to seconds- Output frame: inertial (ECI) for analytical propagators, TEME for SGP4
- Re-exports SatelliteToolboxBase and SatelliteToolboxSgp4
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