satkit
Satellite astrodynamics in Rust, with full Python bindings.
Satkit is a high-performance orbital mechanics library written in Rust with complete Python bindings via PyO3. It handles coordinate transforms, orbit propagation, time systems, gravity models, atmospheric density, and JPL ephemerides -- everything needed for satellite astrodynamics work.
Documentation and tutorials (Python examples, but the concepts and API apply equally to Rust) | Rust API reference | Changelog
Installation
Rust:
cargo add satkit
Python:
pip install satkit
Pre-built wheels are available for Linux (x86_64, aarch64), macOS (Apple silicon), and Windows (x86_64) on Python 3.11--3.15; Intel Macs build from source (pip install --no-binary satkit satkit) or use conda-forge.
The IERS nutation tables and gravity models are compiled in, so frames, gravity, SGP4 and time work with no data files. The JPL ephemeris downloads on first use, and Earth orientation and space weather are fetched on first use and refreshed with satkit.utils.update_datafiles(). See Data Files for directories and offline use.
Quick Examples
SGP4 propagation (Python)
import satkit as sk
tle = sk.TLE.from_lines([
"ISS (ZARYA)",
"1 25544U 98067A 24001.50000000 .00016717 00000-0 10270-3 0 9003",
"2 25544 51.6432 351.4697 0007417 130.5364 329.6482 15.48915330299357"
])[0]
pos, vel = sk.sgp4(tle, sk.time(2024, 1, 2))
High-precision propagation (Python)
import satkit as sk
import numpy as np
r0 = 6378e3 + 500e3 # 500 km altitude
v0 = np.sqrt(sk.consts.mu_earth / r0)
settings = sk.propsettings(
gravity_model=sk.gravmodel.egm2008, # default; also egm96, jgm3, jgm2, itugrace16
gravity_degree=8,
integrator=sk.integrator.rkv98, # default; also rkv87, rkv65, rkts54,
# gauss_jackson8 (fixed-step multistep)
)
result = sk.propagate(
np.array([r0, 0, 0, 0, v0, 0]),
sk.time(2024, 1, 1),
end=sk.time(2024, 1, 1) + sk.duration.from_days(1),
propsettings=settings,
)
state = result.interp(sk.time(2024, 1, 1) + sk.duration.from_hours(6))
Coordinate transforms (Python)
import satkit as sk
time = sk.time(2024, 1, 1, 12, 0, 0)
coord = sk.itrfcoord(latitude_deg=42.0, longitude_deg=-71.0, altitude=100.0)
q = sk.frametransform.qitrf2gcrf(time)
gcrf_pos = q * coord.vector
Planetary ephemerides (Rust)
use satkit::{Instant, SolarSystem, jplephem};
let time = Instant::from_datetime(2024, 1, 1, 0, 0, 0.0)?;
let (pos, vel) = jplephem::geocentric_state(SolarSystem::Moon, &time)?;
Features
Coordinate Frames
Full IERS 2010 Conventions reduction (IAU 2006/2000A precession-nutation) with Earth orientation parameters:
| Frame | Description |
|---|---|
| ITRF | International Terrestrial Reference Frame (Earth-fixed) |
| GCRF | Geocentric Celestial Reference Frame (inertial) |
| TEME | True Equator Mean Equinox (SGP4 output frame) |
| CIRS | Celestial Intermediate Reference System |
| TIRS | Terrestrial Intermediate Reference System |
| EME2000 / ICRF | J2000 mean equator and the International Celestial Reference Frame |
| Geodetic | Latitude / longitude / altitude (WGS-84) |
Plus satellite-local RTN, NTW, and LVLH frames (maneuvers, covariance), and ENU, NED, and geodesic distance (Vincenty) utilities.
Orbit Propagation
- Numerical -- Selectable adaptive Runge-Kutta integrators (9(8), 8(7), 6(5), 5(4)) plus RODAS4 (stiff) and Gauss-Jackson 8 (fixed-step multistep for high-precision long-duration propagation), with dense output, state transition matrix, and configurable force models. With matched force models it agrees with NASA GMAT to a few centimetres over 7 days in LEO, MEO, and GEO (see Testing and Validation)
- SGP4 -- Standard TLE/OMM propagator with TLE fitting from precision states
- Keplerian -- Analytical two-body propagation
Orbit Maneuvers
- Impulsive maneuvers -- Instantaneous delta-v applied at a scheduled time during propagation. Supported frames: GCRF (inertial), RTN (radial/tangential/normal — the CCSDS OEM convention, also exposed as
RSWandRICaliases), NTW (velocity-aligned — natural for prograde burns on eccentric orbits, where a pure +T delta-v adds exactly Δv to |v|), and LVLH (Local Vertical / Local Horizontal). Ergonomic helpersadd_prograde/add_retrograde/add_radial/add_normalfor common scalar-magnitude burns. - Continuous thrust -- Constant-acceleration thrust arcs over time windows in any of the frames above, integrated directly into the force model
- Automatic segmentation -- Propagation through maneuver sequences is handled transparently, including backward propagation
Force Models
- Earth gravity: EGM96, EGM2008, JGM2, JGM3, ITU GRACE16 (spherical harmonics up to degree/order 70; Montenbruck & Gill 2000, §3.2), with tide-system-aware solid tides
- Solid Earth tides: IERS Conventions 2010 §6.2.1 Step-1 corrections to the gravity field
- Third-body gravity: Sun and Moon via JPL DE440/441 ephemerides
- Atmospheric drag: NRLMSISE-00 (Picone et al. 2002) fed automatically from the GFZ Potsdam observed record (observed F10.7 / centred F10.7A and the 7-element 3-hourly geomagnetic ap history, so density responds to storms within hours), then the NOAA/SWPC 45-day and NASA MSAFE monthly forecasts, which carry a climatological Ap years ahead; validated against GMAT (below)
- Solar radiation pressure: Cannonball model with shadow function and inverse-square Sun-distance scaling
- Relativity: IERS 2010 Eq. 10.12 — Schwarzschild, geodesic (de Sitter) precession, and Lense–Thirring
Time Systems
Seamless conversion between UTC, TAI, TT, TDB, UT1, and GPS time scales with full leap-second handling.
Solar System
- JPL DE440/DE441 ephemerides for all planets, Sun, Moon, and barycenters
- Fast analytical Sun/Moon models for lower-precision work
- Sunrise/sunset and Moon phase calculations
Linear Algebra
SatKit uses numeris for all linear algebra (vectors, matrices, quaternions, ODE integration). If you also use nalgebra in your project, enable the nalgebra feature on numeris for zero-cost From/Into conversions between types:
numeris = { version = "0.5.18", features = ["nalgebra"] }
Cargo Features
| Feature | Default | Description |
|---|---|---|
omm-xml |
yes | XML OMM deserialization via quick-xml |
download |
yes | Data-file downloader (update_datafiles) via ureq |
chrono |
no | TimeLike impl for chrono::DateTime |
Testing and Validation
The library is validated against:
- Vallado test cases for SGP4, coordinate transforms, and Keplerian elements
- JPL test vectors for DE440/441 ephemeris interpolation (10,000+ cases)
- NASA GMAT reference trajectories for the high-precision propagator (see below)
- ICGEM reference values for gravity field calculations
- GPS SP3 precise ephemerides for multi-day numerical propagation
The Rust and Python test suites run in CI on Linux, macOS and Windows.
GMAT comparison
The numerical propagator is regression-tested against 25 reference trajectories from NASA's General Mission Analysis Tool (GMAT R2026A), checked in under tests/gmat/: seven-day gravity / third-body / tides / relativity cases from LEO to cislunar distance, and three-day drag cases. With matched force models the two agree to 2–13 cm over 7 days (LEO to GEO), and with drag to 1–2 × 10⁻⁴ of the drag-induced displacement. Details and tolerances: the GMAT validation page and tests/gmat/README.md.
To run the tests locally (data and test-vector downloads, environment variables), see CONTRIBUTING.md.
Documentation
- Rust: docs.rs/satkit
- Python: satkit.dev -- tutorials, Jupyter notebooks, and API reference
References
The primary sources for every model and algorithm — IERS Conventions (2010), Vallado (2013), Montenbruck & Gill (2000), Vallado et al. (2006) for SGP4, Picone et al. (2002) for NRLMSISE-00, Park et al. (2021) for DE440, Verner (2010) and Berry & Healy (2004) for the integrators, Izzo (2015) for Lambert, and the gravity-model reports — are collected with DOIs on the documentation site's References page.
License
Licensed under either of
- Apache License, Version 2.0 (LICENSE-APACHE or http://www.apache.org/licenses/LICENSE-2.0)
- MIT license (LICENSE-MIT or http://opensource.org/licenses/MIT)
at your option.
The gravity models and IERS tables compiled into the library are third-party data (US Government works and IERS tables, all freely redistributable) — see THIRDPARTY-DATA.md. The optional ITU_GRACE16 model (CC BY 4.0) is not part of the library; it is downloaded only when selected.
Contribution
Unless you explicitly state otherwise, any contribution intentionally submitted for inclusion in the work by you, as defined in the Apache-2.0 license, shall be dual licensed as above, without any additional terms or conditions.
1 maintainer
Metadata
1 maintainer
Release files for satkit 0.24.1
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