| Name | satkit JSON |
| Version |
0.8.3
JSON |
| download |
| home_page | None |
| Summary | Satellite Orbital Dynamics Toolkit |
| upload_time | 2025-10-11 19:59:00 |
| maintainer | None |
| docs_url | None |
| author | None |
| requires_python | >=3.8 |
| license | MIT License
Copyright (c) 2025 Steven Michael
Permission is hereby granted, free of charge, to any person obtaining a copy
of this software and associated documentation files (the "Software"), to deal
in the Software without restriction, including without limitation the rights
to use, copy, modify, merge, publish, distribute, sublicense, and/or sell
copies of the Software, and to permit persons to whom the Software is
furnished to do so, subject to the following conditions:
The above copyright notice and this permission notice shall be included in all
copies or substantial portions of the Software.
THE SOFTWARE IS PROVIDED "AS IS", WITHOUT WARRANTY OF ANY KIND, EXPRESS OR
IMPLIED, INCLUDING BUT NOT LIMITED TO THE WARRANTIES OF MERCHANTABILITY,
FITNESS FOR A PARTICULAR PURPOSE AND NONINFRINGEMENT. IN NO EVENT SHALL THE
AUTHORS OR COPYRIGHT HOLDERS BE LIABLE FOR ANY CLAIM, DAMAGES OR OTHER
LIABILITY, WHETHER IN AN ACTION OF CONTRACT, TORT OR OTHERWISE, ARISING FROM,
OUT OF OR IN CONNECTION WITH THE SOFTWARE OR THE USE OR OTHER DEALINGS IN THE
SOFTWARE.
|
| keywords |
satellite
orbit
astrodynamics
sgp4
tle
jpl
ephemeris
|
| VCS |
|
| bugtrack_url |
|
| requirements |
No requirements were recorded.
|
| Travis-CI |
No Travis.
|
| coveralls test coverage |
No coveralls.
|
# Satellite Toolkit with Rust
An accurate, high-performance satellite orbital kinematics toolkit, written in Rust with a sensible interface.
<br/>
Also includes python bindings for *all* functions via via [pyo3](https://pyo3.rs/)
### Github
### Crates.io
### PyPi
## Language Bindings
- **Native Rust** bindings
- **Python bindings** for compiled rust code ... speed of Rust with convenience of Python<br/>
Install with `pip install satkit`<br/>
PyPi includes binary packages for windows, macos (Intel & ARM), and linux. Python documentation is at: <https://satellite-toolkit.readthedocs.io/latest/>
## Features
- High-precision coordinate transforms between:
- International Terrestrial Reference Frame (ITRF)
- Geocentric Celestial Reference Frame (GCRF) using IAU-2000 reduction
- True-Equinox Mean Equator (TEME) frame used in SGP4 propagation of TLEs
- Celestial Intermediate Reference Frame (CIRF)
- Terrestrial Intermediate Reference Frame (TIRF)
- Terrestrial Geodetic frame (latitude, longitude)
- Geodesic distances
- SGP4, and Keplerian orbit propagation
- JPL high-precision planetary ephemerides
- High-order gravity models
- High-precision, high-speed numerical satellite orbit propagation with high-order efficient Runga-Kutta solvers, ability to solve for state transition matrix, and inclusion following forces:
- High-order Earth gravity with multiple models
- Solar gravity
- Lunar gravity
- Drag: NRL MISE-00 density model
- Radiation pressure
## ODE Solvers
The high-precision numerical satellite orbit propagation makes use of adaptive Runga-Kutta methods for integration of ordinary differential equations. The pure-Rust ODE solver is included as part of the library.
The methods use Runga-Kutta pairs for ODE integration and error estimation generated by Jim Verner: [https://www.sfu.ca/~jverner/](https://www.sfu.ca/~jverner/)
## References, Models, and External Software.
### The equations and many of the unit tests underlying this work are drawn from the following sources:
- **"Fundamentals of Astrodynamics and Applications, Fourth Edition"**, D. Vallado, Microcosm Press and Springer, 2013.<br>
[https://celestrak.org/software/vallado-sw.php](https://celestrak.org/software/vallado-sw.php)
- **"Satellite Orbits: Models, Methods, Applications"**, O. Montenbruck and E. Gill, Springer, 2000.<br>
[https://doi.org/10.1007/978-3-642-58351-3](https://doi.org/10.1007/978-3-642-58351-3)
### Data Dependencies
This code makes reference to and relies on models generated by the following:
- **SGP4 Orbit Propagator** - https://celestrak.org/software/tskelso-sw.php<br/>
NORAD / SGP4 orbit propagator used to generate position and velocity states from orbital ephemerides described by Two-Line Element Sets (TLEs). This code base includes a pure-rust translation of the SGP4 orbit propagator
- **NRL MSISE-00 Density Model** - https://ccmc.gsfc.nasa.gov/models/NRLMSIS~00/<br/>
NRL model of air density, including density at high altitudes, used in to compute satellite drag
- **Gravity Models** - http://icgem.gfz-potsdam.de/home<br/>
International Center for Global Earth Models (ICEGM), collection and archive in a common format of all existing global gravity field models
- **Space Weather** - https://celestrak.org/SpaceData/<br/>
Space weather used to modulate the air density used in drag calculations
- **Earth Orientation Parameters** - https://celestrak.org/SpaceData/<br/>
Time-varying Earth orientation parameters used for time epoch conversions and high-precision rotations between the inertial and Earth-fixed coordinate frames
- **IERS Conventions** - https://www.iers.org/IERS/EN/Publications/TechnicalNotes/tn36.html<br/>
International Earth Rotation and Reference Systems Service Technical Note 36 for rotation between inertial and Earth-fixed coordinate systems.
- **JPL Ephemerides** - https://ssd.jpl.nasa.gov/ephem.html<br/>
High-precision ephemerides for solar system bodies (sun, moon, planets) in frame of solar system barycenter
## Verification
The package includes rust test modules and python test modules for verification of nearly all calculations, including but not limited to:
- **JPL Ephemeris** - Via JPL-provided test vectors for Chebychev polynomial calculation
- **SGP4** - Via SGP4 test vectors provided with original C<sup>++</sup> distribution
## Getting Started
### Rust
Simply include the code in your Cargo.toml file to use. Once installed, make sure you run `utils.update_datafiles` to download the most-recent [data files](#data-dependencies) necessary for many calculations. This only needs to be done once, unless more-recent space weather and Earth orientation parameter data is required (these are updated at least daily).
```rust
satkit.utils.update_datafiles()?;
```
### Python
Satkit is available via pypi.org, and can be installed via the `pip` command:
```bash
python -m pip install satkit
```
Binaries are available for Windows (AMD64), Mac (Intel, Apple Silicon) and Linux (x86_64, aarch64) for python versions 3.8 through 3.14.
Once installed, make sure you download the most-recent [data files](#data-dependencies) necessary for many calculations. This only needs to be done once, unless more-recent space weather and Earth orientation parameter data is required (these are updated at least daily).
```python
import satkit as sk
sk.utils.update_datafiles()
```
## Author
Steven Michael (ssmichael@gmail.com)
Please reach out of you find errors in code or calculations, are interested in contributing to this repository, or have suggestions for improvements to the API.
Raw data
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"description": "# Satellite Toolkit with Rust\n\nAn accurate, high-performance satellite orbital kinematics toolkit, written in Rust with a sensible interface.\n<br/>\nAlso includes python bindings for *all* functions via via [pyo3](https://pyo3.rs/)\n\n### Github\n\n\n\n\n\n### Crates.io\n\n\n\n\n### PyPi\n\n\n\n\n\n\n\n\n\n## Language Bindings\n\n- **Native Rust** bindings\n- **Python bindings** for compiled rust code ... speed of Rust with convenience of Python<br/>\n Install with `pip install satkit`<br/>\n PyPi includes binary packages for windows, macos (Intel & ARM), and linux. Python documentation is at: <https://satellite-toolkit.readthedocs.io/latest/>\n\n## Features\n\n- High-precision coordinate transforms between:\n - International Terrestrial Reference Frame (ITRF)\n - Geocentric Celestial Reference Frame (GCRF) using IAU-2000 reduction\n - True-Equinox Mean Equator (TEME) frame used in SGP4 propagation of TLEs\n - Celestial Intermediate Reference Frame (CIRF)\n - Terrestrial Intermediate Reference Frame (TIRF)\n - Terrestrial Geodetic frame (latitude, longitude)\n- Geodesic distances\n- SGP4, and Keplerian orbit propagation\n- JPL high-precision planetary ephemerides\n- High-order gravity models\n- High-precision, high-speed numerical satellite orbit propagation with high-order efficient Runga-Kutta solvers, ability to solve for state transition matrix, and inclusion following forces:\n - High-order Earth gravity with multiple models\n - Solar gravity\n - Lunar gravity\n - Drag: NRL MISE-00 density model\n - Radiation pressure\n\n## ODE Solvers\n\nThe high-precision numerical satellite orbit propagation makes use of adaptive Runga-Kutta methods for integration of ordinary differential equations. The pure-Rust ODE solver is included as part of the library.\n\nThe methods use Runga-Kutta pairs for ODE integration and error estimation generated by Jim Verner: [https://www.sfu.ca/~jverner/](https://www.sfu.ca/~jverner/)\n\n## References, Models, and External Software.\n\n### The equations and many of the unit tests underlying this work are drawn from the following sources:\n\n- **\"Fundamentals of Astrodynamics and Applications, Fourth Edition\"**, D. Vallado, Microcosm Press and Springer, 2013.<br>\n [https://celestrak.org/software/vallado-sw.php](https://celestrak.org/software/vallado-sw.php)\n- **\"Satellite Orbits: Models, Methods, Applications\"**, O. Montenbruck and E. Gill, Springer, 2000.<br>\n [https://doi.org/10.1007/978-3-642-58351-3](https://doi.org/10.1007/978-3-642-58351-3)\n\n### Data Dependencies\n\nThis code makes reference to and relies on models generated by the following:\n\n- **SGP4 Orbit Propagator** - https://celestrak.org/software/tskelso-sw.php<br/>\n NORAD / SGP4 orbit propagator used to generate position and velocity states from orbital ephemerides described by Two-Line Element Sets (TLEs). This code base includes a pure-rust translation of the SGP4 orbit propagator\n- **NRL MSISE-00 Density Model** - https://ccmc.gsfc.nasa.gov/models/NRLMSIS~00/<br/>\n NRL model of air density, including density at high altitudes, used in to compute satellite drag\n- **Gravity Models** - http://icgem.gfz-potsdam.de/home<br/>\n International Center for Global Earth Models (ICEGM), collection and archive in a common format of all existing global gravity field models\n- **Space Weather** - https://celestrak.org/SpaceData/<br/>\n Space weather used to modulate the air density used in drag calculations\n- **Earth Orientation Parameters** - https://celestrak.org/SpaceData/<br/>\n Time-varying Earth orientation parameters used for time epoch conversions and high-precision rotations between the inertial and Earth-fixed coordinate frames\n- **IERS Conventions** - https://www.iers.org/IERS/EN/Publications/TechnicalNotes/tn36.html<br/>\n International Earth Rotation and Reference Systems Service Technical Note 36 for rotation between inertial and Earth-fixed coordinate systems.\n- **JPL Ephemerides** - https://ssd.jpl.nasa.gov/ephem.html<br/>\n High-precision ephemerides for solar system bodies (sun, moon, planets) in frame of solar system barycenter\n\n## Verification\n\nThe package includes rust test modules and python test modules for verification of nearly all calculations, including but not limited to:\n\n- **JPL Ephemeris** - Via JPL-provided test vectors for Chebychev polynomial calculation\n- **SGP4** - Via SGP4 test vectors provided with original C<sup>++</sup> distribution\n\n## Getting Started\n\n### Rust\n\nSimply include the code in your Cargo.toml file to use. Once installed, make sure you run `utils.update_datafiles` to download the most-recent [data files](#data-dependencies) necessary for many calculations. This only needs to be done once, unless more-recent space weather and Earth orientation parameter data is required (these are updated at least daily).\n\n```rust\nsatkit.utils.update_datafiles()?;\n```\n\n\n### Python\n\nSatkit is available via pypi.org, and can be installed via the `pip` command:\n```bash\npython -m pip install satkit\n```\n\nBinaries are available for Windows (AMD64), Mac (Intel, Apple Silicon) and Linux (x86_64, aarch64) for python versions 3.8 through 3.14.\n\nOnce installed, make sure you download the most-recent [data files](#data-dependencies) necessary for many calculations. 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