Expand description
A small Rust port of the MATLAB SGP8 routine found in refs/SGP8/sgp8.m.
The public function sgp8/sgp4 implements the orbital propagator and returns
position (km) and velocity (km/min) vectors.
Structs§
- SatData
- Satellite input parameters required by the SGP ports.
- Vector3
- A simple 3-vector of f64 used for position/velocity results.
Functions§
- actan
- days2mdh
- Convert fractional day-of-year into month, day, hour, minute and second.
- ecef2tod
- Convert TEME state vectors to ECEF (Earth-fixed) coordinates.
- fmod2p
- Parse a TLE pair (line1, line2) and return
SatData. - mjday
- Parse TLE epoch (yyddd.dddddd) from line 1 and return MJD (UTC)
- parse_
tle_ lines - Create
SatDatafrom typical TLE numeric fields. - read_
eop_ for_ mjd - Convert ECEF state vectors to True-Of-Date (TOD) frame.
- satdata_
from_ tle - sgp4
- Port of the MATLAB
sgp4routine (refs/SGP4/sgp4.m). - sgp8
- Port of the MATLAB
sgp8routine. Returns (position_km, velocity_km_per_min) - teme2ecef
- Convert a state from TEME to an ECI-like frame (precession+nutation applied).
- teme2eci
- Compute the sidereal rotation matrix and its time derivative.
- timediff
- Compute several time-scale differences used by the transforms.
- tle_
epoch_ mjd - Wrap angle into the range [0, 2*pi).