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BrcKeplerOrbit Class Reference
[Ephemeris calculations]

#include <BrcKeplerOrbit.hpp>

Inheritance diagram for BrcKeplerOrbit:

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List of all members.

Detailed Description

Orbit information for a single satellite.

This class encapsulates the orbit parameters in any of several navigation message formats (basically those that use Keplerian elements), provides functions to decode the as-broadcast bit-encodings, and generate SV positions as a function of time.

Definition at line 81 of file BrcKeplerOrbit.hpp.

Public Member Functions

 BrcKeplerOrbit () throw ()
 Default constuctor.
 BrcKeplerOrbit (const std::string satSysArg, const ObsID obsIDArg, const short PRNIDArg, const CommonTime beginFitArg, const CommonTime endFitArg, const CommonTime ToeArg, const short URAoeArg, const bool healthyArg, const double CucArg, const double CusArg, const double CrcArg, const double CrsArg, const double CicArg, const double CisArg, const double M0Arg, const double dnArg, const double dndotArg, const double eccArg, const double AArg, const double AhalfArg, const double AdotArg, const double OMEGA0Arg, const double i0Arg, const double wArg, const double OMEGAdotARg, const double idotArg)
 General purpose constructor.
 BrcKeplerOrbit (const ObsID obsIDArg, const short PRNID, const short fullweeknum, const long subframe1[10], const long subframe2[10], const long subframe3[10])
 Legacy GPS Subframe 1-3.
virtual ~BrcKeplerOrbit ()
 Add other constructors for other navigation message formats here.... Destructor.
void loadData (const std::string satSysArg, const ObsID obsIDArg, const short PRNIDArg, const CommonTime beginFitArg, const CommonTime endFitArg, const CommonTime ToeArg, const short URAoeArg, const bool healthyArg, const double CucArg, const double CusArg, const double CrcArg, const double CrsArg, const double CicArg, const double CisArg, const double M0Arg, const double dnArg, const double dndotArg, const double eccArg, const double AArg, const double AhalfArg, const double AdotArg, const double OMEGA0Arg, const double i0Arg, const double wArg, const double OMEGAdotARg, const double idotArg)
 General purpose means to load data into object.
void loadData (const ObsID obsIDArg, const short PRNID, const short fullweeknum, const long subframe1[10], const long subframe2[10], const long subframe3[10]) throw ( InvalidParameter )
 Load data based on the GPS Legacy message.
CommonTime getOrbitEpoch () const throw (InvalidRequest)
 Returns the epoch time (time of ephemeris) from this ephemeris, correcting for half weeks and HOW time.
CommonTime getBeginningOfFitInterval () const throw (InvalidRequest)
 Returns the time at the beginning of the fit interval.
CommonTime getEndOfFitInterval () const throw (InvalidRequest)
 Returns the time at the end of the fit interval.
bool hasData () const
 Return true if orbit data has been loaded.
std::string getSatSystem () const throw (gpstk::InvalidRequest)
 Return satellite system ID.
std::string getSignal () const throw (gpstk::InvalidRequest)
 Return signal type associated with this orbit.
short getPRNID () const throw (gpstk::InvalidRequest)
 This function returns the PRN ID of the SV.
bool isHealthy () const throw (gpstk::InvalidRequest)
 This function returns the health status of the SV.
bool withinFitInterval (const CommonTime) const throw (gpstk::InvalidRequest)
 Return true if fit interval is valid .
short getFullWeek () const throw (gpstk::InvalidRequest)
 This function return the GPS week number for the orbit.
double getAccuracy () const throw (gpstk::InvalidRequest)
 This function returns the value of the SV accuracy (m) computed from the accuracy information contained in the nav message.
void setAccuracy (const double &acc) throw (gpstk::InvalidRequest)
short getURAoe () const throw (gpstk::InvalidRequest)
double getCus () const throw (gpstk::InvalidRequest)
 This function returns the value of the sine latitude harmonic perturbation in radians.
double getCrs () const throw (gpstk::InvalidRequest)
 This function returns the value of the sine radius harmonic perturbation in meters.
double getCis () const throw (gpstk::InvalidRequest)
 This function returns the value of the sine inclination harmonic perturbation in radians.
double getCrc () const throw (gpstk::InvalidRequest)
 This function returns the value of the cosine radius harmonic perturbation in meters.
double getCuc () const throw (gpstk::InvalidRequest)
 This function returns the value of the cosine latitude harmonic perturbation in radians.
double getCic () const throw (gpstk::InvalidRequest)
 This function returns the value of the cosine inclination harmonic perturbation in radians.
double getToe () const throw (gpstk::InvalidRequest)
 This function returns the value of the time of orbit in GPS seconds of week.
double getM0 () const throw (gpstk::InvalidRequest)
 This function returns the value of the mean anomaly in radians.
double getDn () const throw (gpstk::InvalidRequest)
 This function returns the value of the correction to the mean motion in radians/second.
double getDnDot () const throw (gpstk::InvalidRequest)
 This function returns the value of the rate correction to the mean motion in radians/second**2.
double getEcc () const throw (gpstk::InvalidRequest)
 This function returns the value of the eccentricity.
double getA () const throw (gpstk::InvalidRequest)
 This function returns the value of the semi-major axis in meters.
double getAhalf () const throw (gpstk::InvalidRequest)
 This function returns the value of the square root of the semi-major axis in meters**.5.
double getAdot () const throw (gpstk::InvalidRequest)
 This function returns the value of the rate of the semi-major axis in meters/sec.
double getOmega0 () const throw (gpstk::InvalidRequest)
 This function returns the value of the right ascension of the ascending node in radians.
double getI0 () const throw (gpstk::InvalidRequest)
 This function returns the value of the inclination in radians.
double getW () const throw (gpstk::InvalidRequest)
 This function returns the value of the argument of perigee in radians.
double getOmegaDot () const throw (gpstk::InvalidRequest)
 This function returns the value of the rate of the right ascension of the ascending node in radians/second.
double getIDot () const throw (gpstk::InvalidRequest)
 This function returns the value of the rate of the inclination in radians/second.
Xv svXv (const CommonTime &t) const throw (gpstk::InvalidRequest)
 Compute satellite position at the given time using this orbit data.
double svRelativity (const CommonTime &t) const throw ( gpstk::InvalidRequest )
 Compute satellite relativity correction (sec) at the given time
Exceptions:
InvalidRequest if a required subframe has not been stored.

void dump (std::ostream &s=std::cout) const throw ()
 Output the contents of this orbit data to the given stream.

Protected Attributes

bool dataLoaded
 True if data is present, False otherwise.
std::string satSys
 Satellite system ID (as per Rinex).
ObsID obsID
 Defines carrier and tracking code.
short PRNID
 SV PRN ID.
CommonTime Toe
 Orbit epoch.
short URAoe
 SV accuracy Index.
bool healthy
 SV health (healthy=true, other=false.
double Cuc
 Cosine latitude (rad).
double Cus
 Sine latitude (rad).
double Crc
 Cosine radius (m).
double Crs
 Sine radius (m).
double Cic
 Cosine inclination (rad).
double Cis
 Sine inclination (rad).
double M0
 Mean anomaly (rad).
double dn
 Correction to mean motion (rad/sec).
double dndot
 Rate of correction to mean motion (rad/sec/sec).
double ecc
 Eccentricity.
double A
 Semi-major axis (m).
double Ahalf
 Square Root of semi-major axis (m**.5).
double Adot
 Rate of semi-major axis (m/sec).
double OMEGA0
 Rt ascension of ascending node (rad).
double i0
 Inclination (rad).
double w
 Argument of perigee (rad).
double OMEGAdot
 Rate of Rt ascension (rad/sec).
double idot
 Rate of inclination angle (rad/sec).
CommonTime beginFit
 Time at beginning of fit interval.
CommonTime endFit
 Time at end of fit interval.

Friends

std::ostream & operator<< (std::ostream &s, const BrcKeplerOrbit &eph)

Constructor & Destructor Documentation

BrcKeplerOrbit (   )  throw ()
 

Default constuctor.

Definition at line 52 of file BrcKeplerOrbit.cpp.

References BrcKeplerOrbit::A, BrcKeplerOrbit::Adot, BrcKeplerOrbit::Ahalf, BrcKeplerOrbit::Cic, BrcKeplerOrbit::Cis, BrcKeplerOrbit::Crc, BrcKeplerOrbit::Crs, BrcKeplerOrbit::Cuc, BrcKeplerOrbit::Cus, BrcKeplerOrbit::dataLoaded, BrcKeplerOrbit::dn, BrcKeplerOrbit::dndot, BrcKeplerOrbit::ecc, BrcKeplerOrbit::healthy, BrcKeplerOrbit::i0, BrcKeplerOrbit::idot, BrcKeplerOrbit::M0, BrcKeplerOrbit::OMEGA0, BrcKeplerOrbit::OMEGAdot, BrcKeplerOrbit::PRNID, BrcKeplerOrbit::satSys, BrcKeplerOrbit::URAoe, and BrcKeplerOrbit::w.

BrcKeplerOrbit (  const std::string  satSysArg,
const ObsID  obsIDArg,
const short  PRNIDArg,
const CommonTime  beginFitArg,
const CommonTime  endFitArg,
const CommonTime  ToeArg,
const short  URAoeArg,
const bool  healthyArg,
const double  CucArg,
const double  CusArg,
const double  CrcArg,
const double  CrsArg,
const double  CicArg,
const double  CisArg,
const double  M0Arg,
const double  dnArg,
const double  dndotArg,
const double  eccArg,
const double  AArg,
const double  AhalfArg,
const double  AdotArg,
const double  OMEGA0Arg,
const double  i0Arg,
const double  wArg,
const double  OMEGAdotARg,
const double  idotArg
) 
 

General purpose constructor.

Definition at line 69 of file BrcKeplerOrbit.cpp.

References BrcKeplerOrbit::loadData().

BrcKeplerOrbit (  const ObsID  obsIDArg,
const short  PRNID,
const short  fullweeknum,
const long  subframe1[10],
const long  subframe2[10],
const long  subframe3[10]
) 
 

Legacy GPS Subframe 1-3.

Definition at line 90 of file BrcKeplerOrbit.cpp.

References BrcKeplerOrbit::loadData().

virtual ~BrcKeplerOrbit (   )  [inline, virtual]
 

Add other constructors for other navigation message formats here.... Destructor.

Definition at line 121 of file BrcKeplerOrbit.hpp.

Member Function Documentation

void dump (  std::ostream &  s = std::cout  )  const throw ()
 

Output the contents of this orbit data to the given stream.

Definition at line 791 of file BrcKeplerOrbit.cpp.

Referenced by gpstk::operator<<().

double getA (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the semi-major axis in meters.

Definition at line 634 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getA(), and EngEphemeris::setSF3().

double getAccuracy (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the SV accuracy (m) computed from the accuracy information contained in the nav message.

Definition at line 489 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW, gpstk::ura2CNAVaccuracy(), and BrcKeplerOrbit::URAoe.

Referenced by EngEphemeris::getAccuracy(), and CNAVEphemeris::getAccuracy().

double getAdot (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the rate of the semi-major axis in meters/sec.

Definition at line 656 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::setSF3().

double getAhalf (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the square root of the semi-major axis in meters**.5.

Definition at line 645 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getAhalf(), and EngEphemeris::setSF3().

CommonTime getBeginningOfFitInterval (   )  const throw (InvalidRequest)
 

Returns the time at the beginning of the fit interval.

Definition at line 444 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

double getCic (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the cosine inclination harmonic perturbation in radians.

Definition at line 578 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getCic().

double getCis (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the sine inclination harmonic perturbation in radians.

Definition at line 545 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getCis().

double getCrc (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the cosine radius harmonic perturbation in meters.

Definition at line 556 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getCrc().

double getCrs (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the sine radius harmonic perturbation in meters.

Definition at line 534 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getCrs(), and EngEphemeris::setSF3().

double getCuc (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the cosine latitude harmonic perturbation in radians.

Definition at line 567 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getCuc(), and EngEphemeris::setSF3().

double getCus (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the sine latitude harmonic perturbation in radians.

Definition at line 523 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getCus(), and EngEphemeris::setSF3().

double getDn (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the correction to the mean motion in radians/second.

Definition at line 612 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getDn(), and EngEphemeris::setSF3().

double getDnDot (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the rate correction to the mean motion in radians/second**2.

Definition at line 667 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::setSF3().

double getEcc (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the eccentricity.

Definition at line 623 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getEcc(), and EngEphemeris::setSF3().

CommonTime getEndOfFitInterval (   )  const throw (InvalidRequest)
 

Returns the time at the end of the fit interval.

Definition at line 455 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

short getFullWeek (   )  const throw (gpstk::InvalidRequest)
 

This function return the GPS week number for the orbit.

this is the full GPS week (ie > 10 bits).

Definition at line 477 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW, BrcKeplerOrbit::Toe, and GPSWeek::week.

double getI0 (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the inclination in radians.

Definition at line 689 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getI0().

double getIDot (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the rate of the inclination in radians/second.

Definition at line 722 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getIDot().

double getM0 (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the mean anomaly in radians.

Definition at line 601 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getM0(), and EngEphemeris::setSF3().

double getOmega0 (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the right ascension of the ascending node in radians.

Definition at line 678 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getOmega0().

double getOmegaDot (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the rate of the right ascension of the ascending node in radians/second.

Definition at line 711 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getOmegaDot().

CommonTime getOrbitEpoch (   )  const throw (InvalidRequest)
 

Returns the epoch time (time of ephemeris) from this ephemeris, correcting for half weeks and HOW time.

Definition at line 438 of file BrcKeplerOrbit.cpp.

Referenced by EngEphemeris::getEphemerisEpoch().

short getPRNID (   )  const throw (gpstk::InvalidRequest)
 

This function returns the PRN ID of the SV.

Definition at line 466 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

std::string getSatSystem (   )  const throw (gpstk::InvalidRequest)
 

Return satellite system ID.

std::string getSignal (   )  const throw (gpstk::InvalidRequest)
 

Return signal type associated with this orbit.

double getToe (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the time of orbit in GPS seconds of week.

Definition at line 589 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW, GPSWeekSecond::sow, and BrcKeplerOrbit::Toe.

Referenced by EngEphemeris::getToe(), and EngEphemeris::setSF3().

short getURAoe (   )  const throw (gpstk::InvalidRequest)
 

Definition at line 512 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getAccFlag(), CNAVEphemeris::getURAoe(), CNAV2EphClk::getURAoe(), and EngEphemeris::setSF3().

double getW (   )  const throw (gpstk::InvalidRequest)
 

This function returns the value of the argument of perigee in radians.

Definition at line 700 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Referenced by EngEphemeris::getW().

bool hasData (   )  const
 

Return true if orbit data has been loaded.

Definition at line 242 of file BrcKeplerOrbit.cpp.

Referenced by EngEphemeris::getOrbit(), CNAVEphemeris::getOrbit(), and CNAV2EphClk::getOrbit().

bool isHealthy (   )  const throw (gpstk::InvalidRequest)
 

This function returns the health status of the SV.

Definition at line 247 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

void loadData (  const ObsID  obsIDArg,
const short  PRNID,
const short  fullweeknum,
const long  subframe1[10],
const long  subframe2[10],
const long  subframe3[10]
)  throw ( InvalidParameter )
 

Load data based on the GPS Legacy message.

Definition at line 144 of file BrcKeplerOrbit.cpp.

References gpstk::getLegacyFitInterval(), and GPSTK_THROW.

void loadData (  const std::string  satSysArg,
const ObsID  obsIDArg,
const short  PRNIDArg,
const CommonTime  beginFitArg,
const CommonTime  endFitArg,
const CommonTime  ToeArg,
const short  URAoeArg,
const bool  healthyArg,
const double  CucArg,
const double  CusArg,
const double  CrcArg,
const double  CrsArg,
const double  CicArg,
const double  CisArg,
const double  M0Arg,
const double  dnArg,
const double  dndotArg,
const double  eccArg,
const double  AArg,
const double  AhalfArg,
const double  AdotArg,
const double  OMEGA0Arg,
const double  i0Arg,
const double  wArg,
const double  OMEGAdotARg,
const double  idotArg
) 
 

General purpose means to load data into object.

Definition at line 101 of file BrcKeplerOrbit.cpp.

References BrcKeplerOrbit::A, BrcKeplerOrbit::Adot, BrcKeplerOrbit::Ahalf, BrcKeplerOrbit::beginFit, BrcKeplerOrbit::Cic, BrcKeplerOrbit::Cis, BrcKeplerOrbit::Crc, BrcKeplerOrbit::Crs, BrcKeplerOrbit::Cuc, BrcKeplerOrbit::Cus, BrcKeplerOrbit::dataLoaded, BrcKeplerOrbit::dn, BrcKeplerOrbit::dndot, BrcKeplerOrbit::ecc, BrcKeplerOrbit::endFit, BrcKeplerOrbit::healthy, BrcKeplerOrbit::i0, BrcKeplerOrbit::idot, BrcKeplerOrbit::M0, BrcKeplerOrbit::obsID, BrcKeplerOrbit::OMEGA0, BrcKeplerOrbit::OMEGAdot, BrcKeplerOrbit::PRNID, BrcKeplerOrbit::satSys, BrcKeplerOrbit::Toe, BrcKeplerOrbit::URAoe, and BrcKeplerOrbit::w.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), EngEphemeris::loadData(), CNAVEphemeris::loadData(), CNAV2EphClk::loadData(), Rinex3NavData::operator EngEphemeris(), EngEphemeris::setSF1(), EngEphemeris::setSF2(), and EngEphemeris::unifiedConvert().

void setAccuracy (  const double &  acc  )  throw (gpstk::InvalidRequest)
 

Definition at line 501 of file BrcKeplerOrbit.cpp.

References gpstk::accuracy2ura(), and GPSTK_THROW.

double svRelativity (  const CommonTime &  t  )  const throw ( gpstk::InvalidRequest )
 

Compute satellite relativity correction (sec) at the given time

Exceptions:
InvalidRequest if a required subframe has not been stored.

Definition at line 412 of file BrcKeplerOrbit.cpp.

References ABS, GPSEllipsoid::gm(), gpstk::REL_CONST, and SQRT.

Referenced by CNAV2EphClk::svRelativity().

Xv svXv (  const CommonTime &  t  )  const throw (gpstk::InvalidRequest)
 

Compute satellite position at the given time using this orbit data.

Exceptions:
InvalidRequest if a required subframe has not been stored.

Definition at line 270 of file BrcKeplerOrbit.cpp.

References GPSEllipsoid::angVelocity(), GPSEllipsoid::gm(), GPSWeekSecond::sow, SQRT, Xv::v, and Xv::x.

Referenced by CNAVEphemeris::svXv().

bool withinFitInterval (  const   CommonTime  )  const throw (gpstk::InvalidRequest)
 

Return true if fit interval is valid .

Definition at line 258 of file BrcKeplerOrbit.cpp.

References GPSTK_THROW.

Friends And Related Function Documentation

std::ostream& operator<< (  std::ostream &  s,
const BrcKeplerOrbit &  eph
)  [friend]
 

Member Data Documentation

double A [protected]
 

Semi-major axis (m).

Definition at line 307 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double Adot [protected]
 

Rate of semi-major axis (m/sec).

Definition at line 309 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double Ahalf [protected]
 

Square Root of semi-major axis (m**.5).

Definition at line 308 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

CommonTime beginFit [protected]
 

Time at beginning of fit interval.

Definition at line 319 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::loadData().

double Cic [protected]
 

Cosine inclination (rad).

Definition at line 297 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double Cis [protected]
 

Sine inclination (rad).

Definition at line 298 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double Crc [protected]
 

Cosine radius (m).

Definition at line 295 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double Crs [protected]
 

Sine radius (m).

Definition at line 296 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double Cuc [protected]
 

Cosine latitude (rad).

Definition at line 293 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double Cus [protected]
 

Sine latitude (rad).

Definition at line 294 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

bool dataLoaded [protected]
 

True if data is present, False otherwise.

Definition at line 282 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double dn [protected]
 

Correction to mean motion (rad/sec).

Definition at line 304 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double dndot [protected]
 

Rate of correction to mean motion (rad/sec/sec).

Definition at line 305 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double ecc [protected]
 

Eccentricity.

Definition at line 306 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

CommonTime endFit [protected]
 

Time at end of fit interval.

Definition at line 320 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::loadData().

bool healthy [protected]
 

SV health (healthy=true, other=false.

Definition at line 288 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double i0 [protected]
 

Inclination (rad).

Definition at line 311 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double idot [protected]
 

Rate of inclination angle (rad/sec).

Definition at line 314 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double M0 [protected]
 

Mean anomaly (rad).

Definition at line 303 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

ObsID obsID [protected]
 

Defines carrier and tracking code.

Definition at line 284 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::loadData().

double OMEGA0 [protected]
 

Rt ascension of ascending node (rad).

Definition at line 310 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

double OMEGAdot [protected]
 

Rate of Rt ascension (rad/sec).

Definition at line 313 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

short PRNID [protected]
 

SV PRN ID.

Definition at line 285 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

std::string satSys [protected]
 

Satellite system ID (as per Rinex).

Definition at line 283 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

CommonTime Toe [protected]
 

Orbit epoch.

Definition at line 286 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::getFullWeek(), BrcKeplerOrbit::getToe(), and BrcKeplerOrbit::loadData().

short URAoe [protected]
 

SV accuracy Index.

Definition at line 287 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), BrcKeplerOrbit::getAccuracy(), and BrcKeplerOrbit::loadData().

double w [protected]
 

Argument of perigee (rad).

Definition at line 312 of file BrcKeplerOrbit.hpp.

Referenced by BrcKeplerOrbit::BrcKeplerOrbit(), and BrcKeplerOrbit::loadData().

The documentation for this class was generated from the following files:
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