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#