“SatKit”
SatKit is a python library providing tools that enable computation and prediction of satellite orbits, satellite maneuvers, and (soon) satellite attitude dynamics.
The SatKit core code is written in rust for speed and safety. The python bindings are done via the pyo3 package. All calculations are performed natively in rust, making the package much faster than a pure-python equivalent.
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 standard Runga-Kutta methods for integration of ordinary differential equations. The 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/
Table of Contents
Basics
User Documentation
Examples
API Reference
- Time Representation
- Quaternions
- Introduction
- Class Reference
quaternionquaternion.__init__()quaternion.__mul__()quaternion.angle()quaternion.as_euler()quaternion.as_rotation_matrix()quaternion.axis()quaternion.conj()quaternion.conjugate()quaternion.from_axis_angle()quaternion.from_rotation_matrix()quaternion.rotation_between()quaternion.rotx()quaternion.roty()quaternion.rotz()quaternion.slerp()
- Coordinate Frame Transforms
- High-Precision Orbit Propagator
- JPL Ephemeris
- ITRF (International Terrestrial Reference Frame) Coordinate
- Earth Gravity Models
- Satellite State Representation
- Two-Line Element Sets and SGP-4
- Constants
- Kepleriean orbital elements
- Utility Functions
- Air Density Model(s)