nav package#
Submodules#
nav.atmosphere module#
nav.ephemeris module#
ephemeris.py
file |
sturdr/nav/ephemeris.py |
brief |
Satellite ephemeris navigation module. |
date |
October 2024 |
refs |
|
- nav.ephemeris.CheckTime(t)#
- class nav.ephemeris.KeplerianEphemeris#
Bases:
object
- Attributes:
- af0
- af1
- af2
- cic
- cis
- crc
- crs
- cuc
- cus
- deltan
- e
- health
- i0
- iDot
- iodc
- iode
- m0
- omega
- omega0
- omegaDot
- sqrtA
- tgd
- toc
- toe
- ura
Methods
GetNavStates
(TOW[, calc_accel])Calculates satellite position, velocity, and acceleration given Keplerian ephemeris elements.
UpdateParameters
(**kwargs)Updates the set of ephemeris parameters based on user inputs
- GetNavStates(TOW: float64, calc_accel: bool = False)#
Calculates satellite position, velocity, and acceleration given Keplerian ephemeris elements.
- Parameters:
- TOWnp.double
Current time of week of measurements [s]
- calc_accelbool, optional
Should acceleration be calculated?, by default False
- Returns:
- posnp.ndarray
Satellite position [m]
- velnp.ndarray
Satellite velocity [m]
- accnp.ndarray
Satellite acceleratio [m]
- UpdateParameters(**kwargs)#
Updates the set of ephemeris parameters based on user inputs
- Raises:
- ValueError
Invalid Keplerian Ephemeris parameter
- af0: float64#
- af1: float64#
- af2: float64#
- cic: float64#
- cis: float64#
- crc: float64#
- crs: float64#
- cuc: float64#
- cus: float64#
- deltan: float64#
- e: float64#
- health: float64#
- i0: float64#
- iDot: float64#
- iodc: float64#
- iode: float64#
- m0: float64#
- omega: float64#
- omega0: float64#
- omegaDot: float64#
- sqrtA: float64#
- tgd: float64#
- toc: float64#
- toe: float64#
- ura: float64#
nav.gps_lnav module#
gps_lnav.py
file |
sturdr/nav/gps_lnav.py |
brief |
Implementation of channel.py for GPS L1 C/A signals. |
date |
October 2024 |
refs |
|
- class nav.gps_lnav.GpsLnavParser#
Bases:
KeplerianEphemeris
- Attributes:
- TOW
- af0
- af1
- af2
- bit_count
- cic
- cis
- crc
- crs
- cuc
- cus
- deltan
- e
- health
- i0
- iDot
- iodc
- iode
- m0
- omega
- omega0
- omegaDot
- signalID
- sqrtA
- subframe
- subframe1
- subframe2
- subframe3
- tgd
- toc
- toe
- ura
- week
- word_count
Methods
GetNavStates
(TOW[, calc_accel])Calculates satellite position, velocity, and acceleration given Keplerian ephemeris elements.
UpdateParameters
(**kwargs)Updates the set of ephemeris parameters based on user inputs
LoadPreamble
LoadSubframe1
LoadSubframe2
LoadSubframe3
LoadSubframe4
LoadSubframe5
NextBit
ParityCheck
ParseSubframe
- LoadPreamble()#
- LoadSubframe1()#
- LoadSubframe2()#
- LoadSubframe3()#
- LoadSubframe4()#
- LoadSubframe5()#
- NextBit(bit: bool)#
- ParityCheck(gpsword: uint32)#
- ParseSubframe()#
- TOW: float64#
- bit_count: int#
- signalID#
- subframe: ndarray#
- subframe1: bool#
- subframe2: bool#
- subframe3: bool#
- week: int#
- word_count: int#