Earth Observation Mission CFI Software Orbit Software User Manual |
Class that stores the orbit data. More...
Public Member Functions | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, double time, long orbit0, long driftMode, double ascMlstDrift, double inclination, long irep, long icyc, double rlong, double ascMlst) throw (CfiError) | |
Class constructor: using orbital parameters. | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, double time, long orbit0, const RefOrbitInfo &refOrbitInfo) throw (CfiError) | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, double time, double pos[3], double vel[3], long absOrbit) throw (CfiError) | |
Class constructor: using state vector. | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, long orbitFileMode, const vector< string > &inputFiles, long timeInitMode, double time0, double time1, long orbit0, long orbit1) throw (CfiError) | |
Class constructor: using orbit file. | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, double time, double pos[3], double vel[3], long absOrbit, const PropagPreciseConf &preciseConf) throw (CfiError) | |
Class constructor: numerical propagator using state vector. | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, long orbitFileMode, const vector< string > &inputFiles, long timeInitMode, double time0, double time1, long orbit0, long orbit1, const PropagPreciseConf &preciseConf) throw (CfiError) | |
Class constructor: numerical propagator using orbit file. | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, long orbitFileMode, vector< OsfFile > &osfData, long timeInitMode, double time0, double time1, long orbit0, long orbit1) throw (CfiError) | |
Class constructor: using data read from OSF. | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, long orbitFileMode, vector< OrbitFile > &osvData, long timeInitMode, double time0, double time1, long orbit0, long orbit1) throw (CfiError) | |
Class constructor: using data read from Orbit files (POF or ROF). | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, long orbitFileMode, vector< DorisFile > &dorisData, long timeInitMode, double time0, double time1, long orbit0, long orbit1) throw (CfiError) | |
Class constructor: using data read from DORIS files. | |
OrbitId (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, const GeoOrbitInitData &geoOrbitInit) throw (CfiError) | |
OrbitId (OrbitId &orbitIdIn) | |
Copy constructor. | |
~OrbitId () throw (CfiError) | |
Class destructor. | |
void | init (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, double time, long orbit0, long driftMode, double ascMlstDrift, double inclination, long irep, long icyc, double rlong, double ascMlst) throw (CfiError) |
Initialise the orbit using orbital parameters. | |
void | init (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, double time, long orbit0, const RefOrbitInfo &refOrbitInfo) throw (CfiError) |
Class constructor: using orbital parameters with support for MLST non linear drift. | |
void | init (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, double time, double pos[3], double vel[3], long absOrbit) throw (CfiError) |
Initialise the orbit using state vector. | |
void | init (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, long orbitFileMode, const vector< string > &inputFiles, long timeInitMode, double time0, double time1, long orbit0, long orbit1) throw (CfiError) |
Initialise the orbit using orbit files. | |
void | init (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, double time, double pos[3], double vel[3], long absOrbit, const PropagPreciseConf &preciseConf) throw (CfiError) |
Initialise the orbit using state vector with numerical propagator. | |
void | init (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, long timeRef, long orbitFileMode, const vector< string > &inputFiles, long timeInitMode, double time0, double time1, long orbit0, long orbit1, const PropagPreciseConf &preciseConf) throw (CfiError) |
Initialise the orbit using orbit file with numerical propagator. | |
void | init (const SatId &satId, const ModelId &modelId, const TimeCorrelation &timeCor, const GeoOrbitInitData &geoOrbitInit) throw (CfiError) |
SatId | satId () const |
Return satellite id. | |
vector< OsvRec > | getOsv () const |
Returns the list of orbit state vectors stored in the OrbitId object. | |
void | setOsv (const vector< OsvRec > &osvRecList) |
Sets the list of orbit state vectors stored in the OrbitId object. | |
vector< ANXExtra > | getAnx () const |
Returns the list of ANX data stored in the OrbitId object. | |
void | setAnx (const vector< ANXExtra > &anxList) |
Sets the list of ANX data stored in the OrbitId object. | |
vector< OsfRecords > | getOsf () const |
Returns the list of orbital changes stored in the OrbitId object. | |
void | setOsf (const vector< OsfRecords > &osvRecList) |
Sets the list of orbital changes stored in the OrbitId object. | |
ValidityTime | getValTime () const |
Returns validity times. | |
void | setValTime (const ValidityTime &valTime) |
Sets validity times. | |
PropagPreciseConf | getPrecisePropagConfig () const throw (CfiError) |
Get numerical propagator configuration. | |
void | setPrecisePropagConfig (const PropagPreciseConf &preciseConf) |
Set numerical propagator configuration. | |
void | setGeoOrbitInfo (const GeoOrbitInfo &geoOrbitInfo) throw (CfiError) |
Set geostationary satellite information. | |
GeoOrbitInfo | getGeoOrbitInfo () throw (CfiError) |
Get geostationary satellite information. | |
OrbitalInfo | getOrbitInfo (long absoluteOrbit) const throw (CfiError) |
Returns orbital information for a requested orbit. | |
OrbitInfo | getOrbitNumbersFromRel (long relOrbit, long cycle) const throw (CfiError) |
Get orbit absolute orbit and phase number from the relative orbit. | |
OrbitInfo | getOrbitNumbersFromPhase (long phase) const throw (CfiError) |
Get orbit absolute and relative orbit from the input phase number. | |
OrbitInfo | getOrbitNumbersFromAbs (long absOrbit) const throw (CfiError) |
Get orbit relative orbit and phase from the input absolute orbit. | |
StateVector | osvCompute (long mode, long timeRef, double time) const throw (CfiError) |
Computes a satellite state vector for a given time. | |
StateVectorExtraInfo | osvComputeExtra (long extraChoice) const throw (CfiError) |
Get orbital auxiliary data for the satellite state vector computed with osvCompute. | |
StateVector | positionOnOrbitToTime (long abs_orbit_number, long angle_type, double angle, double angle_rate, double angle_rate_rate, long deriv, long time_ref) const throw (CfiError) |
Calculates the time, position and velocity vectors in Earth-Fixed associated to a given position on orbit. | |
TleRec | osvToTle (long timeMode, long timeRef, double time0, double time1, long orbit0, long orbit1) throw (CfiError) |
Generates a TLE by fitting the set of orbit state vectors stored in the orbit_id. | |
void | operator= (const OrbitId &orbitIdIn) |
Copy operator. | |
Protected Member Functions | |
OrbitId () | |
Empty class constructor: do not initialise orbit id. |
Class that stores the orbit data.
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
double | time, | |||
long | orbit0, | |||
long | driftMode, | |||
double | ascMlstDrift, | |||
double | inclination, | |||
long | irep, | |||
long | icyc, | |||
double | rlong, | |||
double | ascMlst | |||
) | throw (CfiError) |
Class constructor: using orbital parameters.
This method is deprecated. Use the one that uses a RefOrbitInfo object to introduce orbital parameters.
In order to obtain results consistent with that obtained with an Orbit Scenario file, the drift_mode flag has to be set to drift_mode = XO_NOSUNSYNC_DRIFT + XO_NOSUNSYNC_USE_SIM_MODEL.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum). | |
time | Reference time (Decimal days - Processing format). | |
orbit0 | Absolute orbit number of the reference orbit. | |
driftMode | Flag to select between mlst and inclination as input characterization of reference orbit. Allowed values:
. | |
ascMlstDrift | Drift in mlst of the reference orbit [seconds/day]. | |
inclination | Inclination of the reference orbit [deg]. Allowed range = [0, 180]. | |
irep | Repeat cycle of the reference orbit [days]. Allowed range: > 0. | |
icyc | Cycle length of the reference orbit [orbits]. Allowed range: > 0. | |
rlong | Geocentric longitude of the ascending node (EF RF) [deg]. Allowed range = [0, 360) | |
ascMlst | MLST at ascending node [Decimal hours]. Allowed range = [0, 24). |
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
double | time, | |||
long | orbit0, | |||
const RefOrbitInfo & | refOrbitInfo | |||
) | throw (CfiError) |
Class constructor: using orbital parameters with support for MLST non linear drift. In order to obtain results consistent with that obtained with an Orbit Scenario file, the drift_mode flag has to be set to drift_mode = XO_NOSUNSYNC_DRIFT + XO_NOSUNSYNC_USE_SIM_MODEL.
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
double | time, | |||
double | pos[3], | |||
double | vel[3], | |||
long | absOrbit | |||
) | throw (CfiError) |
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
const vector< string > & | inputFiles, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throw (CfiError) |
Class constructor: using orbit file.
In order to read files, this method internally uses Data Handling functions. Please refer to [D_H_SUM] for further details.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum. When using DORIS Navigator files and time_mode is XOCFI_SEL_TIME, only XOCFI_TIME_UTC is allowed.). | |
orbitFileMode | Flag that indicates the type of the input orbit file (OrbitInitModeEnum except PRECISE models).
. | |
inputFiles | Vector of orbit files. | |
timeInitMode | Flag for selecting the time range of the initialisation (XOCFI_SEL_FILE, XOCFI_SEL_TIME, XOCFI_SEL_ORBIT. For DORIS Navigator files, XOCFI_SEL_ORBIT is not allowed). For TLE files, the whole file is always selected (this flag and the parameters time0/time1, orbit0/orbit1 are dummies). | |
time0 | Start time [Decimal days (Processing format)]. | |
time1 | Stop time [Decimal days (Processing format)]. | |
orbit0 | Start orbit. | |
orbit1 | Stop orbit. |
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
double | time, | |||
double | pos[3], | |||
double | vel[3], | |||
long | absOrbit, | |||
const PropagPreciseConf & | preciseConf | |||
) | throw (CfiError) |
Class constructor: numerical propagator using state vector.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum). | |
time | Time (Decimal days - Processing format). | |
pos | Position vector [m]. | |
vel | Velocity vector [m/s]. | |
absOrbit | Absolute orbit. | |
preciseConf | Numerical propagator configuration. Allowed range for some members:
. |
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
const vector< string > & | inputFiles, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1, | |||
const PropagPreciseConf & | preciseConf | |||
) | throw (CfiError) |
Class constructor: numerical propagator using orbit file.
In order to read files, this method internally uses Data Handling functions. Please refer to [D_H_SUM] for further details.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum. When using DORIS Navigator files and time_mode is XOCFI_SEL_TIME, only XOCFI_TIME_UTC is allowed.). | |
orbitFileMode | Flag that indicates the type of the input orbit file (OrbitInitModeEnum ONLY PRECISE models).
. | |
inputFiles | Vector of orbit files. | |
timeInitMode | Flag for selecting the time range of the initialisation (XOCFI_SEL_FILE, XOCFI_SEL_TIME, XOCFI_SEL_ORBIT. For DORIS Navigator files, XOCFI_SEL_ORBIT is not allowed). For TLE files, the whole file is always selected (this flag and the parameters time0/time1, orbit0/orbit1 are dummies). | |
time0 | Start time [Decimal days (Processing format)]. | |
time1 | Stop time [Decimal days (Processing format)]. | |
orbit0 | Start orbit. | |
orbit1 | Stop orbit. | |
preciseConf | Numerical propagator configuration. Allowed range for some members:
. |
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
vector< OsfFile > & | osfData, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throw (CfiError) |
Class constructor: using data read from OSF.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum). | |
orbitFileMode | Flag that indicates the type of the input orbit file (OrbitInitModeEnum). Allowed values:
. | |
osfData | Vector of OsfFile data. | |
timeInitMode | Flag for selecting the time range of the initialisation (XOCFI_SEL_FILE, XOCFI_SEL_TIME, XOCFI_SEL_ORBIT.). | |
time0 | Start time [Decimal days (Processing format)]. Only used if timeInitMode = XOCFI_SEL_TIME | |
time1 | Stop time [Decimal days (Processing format)].Only used if timeInitMode = XOCFI_SEL_TIME | |
orbit0 | Start orbit. Only used if timeInitMode = XOCFI_SEL_ORBIT | |
orbit1 | Stop orbit. Only used if timeInitMode = XOCFI_SEL_ORBIT |
References EECFI::CfiError::addMsg().
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
vector< OrbitFile > & | osvData, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throw (CfiError) |
Class constructor: using data read from Orbit files (POF or ROF).
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum). | |
orbitFileMode | Flag that indicates the type of the input orbit file (OrbitInitModeEnum). Allowed values:
. | |
osvData | Vector of OrbitFile data. | |
timeInitMode | Flag for selecting the time range of the initialisation (XOCFI_SEL_FILE, XOCFI_SEL_TIME, XOCFI_SEL_ORBIT.). | |
time0 | Start time [Decimal days (Processing format)]. Only used if timeInitMode = XOCFI_SEL_TIME | |
time1 | Stop time [Decimal days (Processing format)].Only used if timeInitMode = XOCFI_SEL_TIME | |
orbit0 | Start orbit. Only used if timeInitMode = XOCFI_SEL_ORBIT | |
orbit1 | Stop orbit. Only used if timeInitMode = XOCFI_SEL_ORBIT |
References EECFI::CfiError::addMsg().
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
vector< DorisFile > & | dorisData, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throw (CfiError) |
Class constructor: using data read from DORIS files.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum. if timeInitMode is XOCFI_SEL_TIME, only XOCFI_TIME_UTC is allowed.). | |
orbitFileMode | Flag that indicates the type of the input orbit file (OrbitInitModeEnum). Allowed values:
. | |
dorisData | Vector of DorisFile data. | |
timeInitMode | Flag for selecting the time range of the initialisation (Allowed values: XOCFI_SEL_FILE, XOCFI_SEL_TIME). | |
time0 | Start time [Decimal days (Processing format)]. Only used if timeInitMode = XOCFI_SEL_TIME | |
time1 | Stop time [Decimal days (Processing format)].Only used if timeInitMode = XOCFI_SEL_TIME | |
orbit0 | Start orbit. Only used if timeInitMode = XOCFI_SEL_ORBIT | |
orbit1 | Stop orbit. Only used if timeInitMode = XOCFI_SEL_ORBIT |
References EECFI::CfiError::addMsg().
EECFI::OrbitId::OrbitId | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
const GeoOrbitInitData & | geoOrbitInit | |||
) | throw (CfiError) |
Class constructor: intialization with geostationary satellite. The only input geodetic coordinate taken into account in initialization is the geocentric longitude; the latitude is set to 0. degrees and the altitude is set to 35786 km independently of the inputs.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
geoOrbitInit | Geostationary satellite initialization information. |
EECFI::OrbitId::OrbitId | ( | OrbitId & | orbitIdIn | ) |
Copy constructor.
orbitIdIn | Orbit Id to be copied. |
EECFI::OrbitId::~OrbitId | ( | ) | throw (CfiError) |
Class destructor.
EECFI::OrbitId::OrbitId | ( | ) | [protected] |
Empty class constructor: do not initialise orbit id.
vector< ANXExtra > EECFI::OrbitId::getAnx | ( | ) | const |
Returns the list of ANX data stored in the OrbitId object.
References EECFI::CfiError::addMsg(), and EECFI::CfiClass::throwWarn.
GeoOrbitInfo EECFI::OrbitId::getGeoOrbitInfo | ( | ) | throw (CfiError) |
Get geostationary satellite information.
References EECFI::CfiError::addMsg(), EECFI::GeoGeodCoord::gcLongitude, EECFI::GeoGeodCoord::gdAltitude, EECFI::GeoGeodCoord::gdLatitude, EECFI::GeoOrbitInfo::geodCoord, and EECFI::CfiClass::throwWarn.
OrbitalInfo EECFI::OrbitId::getOrbitInfo | ( | long | absoluteOrbit | ) | const throw (CfiError) |
Returns orbital information for a requested orbit.
absoluteOrbit | Absolute orbit |
References EECFI::OrbitalInfo::absOrbit, EECFI::OrbitalInfo::cycLength, EECFI::OrbitalInfo::meanKep, EECFI::OrbitalInfo::mlst, EECFI::OrbitalInfo::mlstDrift, EECFI::OrbitalInfo::nodalPeriod, EECFI::OrbitalInfo::oscKep, EECFI::OrbitalInfo::phasing, EECFI::OrbitalInfo::posAnx, EECFI::OrbitalInfo::repCycle, EECFI::OrbitalInfo::utcAnx, and EECFI::OrbitalInfo::velAnx.
Get orbit relative orbit and phase from the input absolute orbit.
absOrbit | Absolute orbit. |
References EECFI::OrbitInfo::absOrbit, EECFI::OrbitInfo::cycle, EECFI::OrbitInfo::phase, and EECFI::OrbitInfo::relOrbit.
Get orbit absolute and relative orbit from the input phase number.
phase | Phase of orbit. |
References EECFI::OrbitInfo::absOrbit, EECFI::OrbitInfo::cycle, EECFI::OrbitInfo::phase, and EECFI::OrbitInfo::relOrbit.
OrbitInfo EECFI::OrbitId::getOrbitNumbersFromRel | ( | long | relOrbit, | |
long | cycle | |||
) | const throw (CfiError) |
Get orbit absolute orbit and phase number from the relative orbit.
relOrbit | Relative orbit | |
cycle | Cycle of orbit. |
References EECFI::OrbitInfo::absOrbit, EECFI::OrbitInfo::cycle, EECFI::OrbitInfo::phase, and EECFI::OrbitInfo::relOrbit.
Referenced by EECFI::RelANXTime::toAbsolute().
vector< OsfRecords > EECFI::OrbitId::getOsf | ( | ) | const |
Returns the list of orbital changes stored in the OrbitId object.
References EECFI::OrbitInfo::absOrbit, EECFI::CfiError::addMsg(), EECFI::OsfRecords::anxInfo, EECFI::RefOrbitInfo::AnxLong, EECFI::AnxInfo::anxPos, EECFI::AnxInfo::anxTai, EECFI::AnxInfo::anxUt1, EECFI::AnxInfo::anxUtc, EECFI::AnxInfo::anxVel, EECFI::OrbitInfo::cycle, EECFI::RefOrbitInfo::cycleLength, EECFI::RefOrbitInfo::driftMode, EECFI::RefOrbitInfo::inclination, EECFI::AnxInfo::kepl, EECFI::MlstNonlinearDrift::linearApproxValidity, EECFI::OsfRecords::missionInfo, EECFI::RefOrbitInfo::mlst, EECFI::RefOrbitInfo::mlstDrift, EECFI::MlstNonlinearDrift::mlstHarmonics, EECFI::RefOrbitInfo::mlstNonlinearDrift, EECFI::OrbitInfo::phase, EECFI::MlstNonlinearDrift::quadraticTerm, EECFI::OsfRecords::refOrbitinfo, EECFI::OrbitInfo::relOrbit, EECFI::RefOrbitInfo::repCycle, EECFI::CfiClass::throwWarn, and EECFI::AnxInfo::tNod.
vector< OsvRec > EECFI::OrbitId::getOsv | ( | ) | const |
Returns the list of orbit state vectors stored in the OrbitId object.
References EECFI::CfiError::addMsg(), and EECFI::CfiClass::throwWarn.
PropagPreciseConf EECFI::OrbitId::getPrecisePropagConfig | ( | ) | const throw (CfiError) |
Get numerical propagator configuration.
References EECFI::CfiError::addMsg(), EECFI::PropagPreciseConf::ap, EECFI::PropagPreciseConf::atmosFlag, EECFI::PropagPreciseConf::f107, EECFI::PropagPreciseConf::f107a, EECFI::PropagPreciseConf::gravDegree, EECFI::PropagPreciseConf::gravFile, EECFI::PropagPreciseConf::gravityFlag, EECFI::PropagPreciseConf::gravOrder, EECFI::PropagPreciseConf::modelsPath, EECFI::PropagPreciseConf::scDragArea, EECFI::PropagPreciseConf::scDragCoeff, EECFI::PropagPreciseConf::scMass, EECFI::PropagPreciseConf::scSrpArea, EECFI::PropagPreciseConf::scSrpCoeff, EECFI::PropagPreciseConf::sgaApFile, EECFI::PropagPreciseConf::sgaF107File, EECFI::PropagPreciseConf::sgaFlag, EECFI::PropagPreciseConf::srpFlag, EECFI::PropagPreciseConf::step, EECFI::PropagPreciseConf::thirdbodyFlag, EECFI::CfiClass::throwWarn, and EECFI::PropagPreciseConf::userFlag.
ValidityTime EECFI::OrbitId::getValTime | ( | ) | const |
Returns validity times.
References EECFI::CfiError::addMsg(), and EECFI::CfiClass::throwWarn.
void EECFI::OrbitId::init | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
double | time, | |||
long | orbit0, | |||
const RefOrbitInfo & | refOrbitInfo | |||
) | throw (CfiError) |
Class constructor: using orbital parameters with support for MLST non linear drift.
void EECFI::OrbitId::init | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
const vector< string > & | inputFiles, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throw (CfiError) |
Initialise the orbit using orbit files.
In order to read files, this method internally uses Data Handling functions. Please refer to [D_H_SUM] for further details.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum. When using DORIS Navigator files and time_mode is XOCFI_SEL_TIME, only XOCFI_TIME_UTC is allowed.). | |
orbitFileMode | Flag that indicates the type of the input orbit file (OrbitInitModeEnum except PRECISE models).
. | |
inputFiles | Vector of orbit files. | |
timeInitMode | Flag for selecting the time range of the initialisation (XOCFI_SEL_FILE, XOCFI_SEL_TIME, XOCFI_SEL_ORBIT. For DORIS Navigator files, XOCFI_SEL_ORBIT is not allowed). For TLE files, the whole file is always selected (this flag and the parameters time0/time1, orbit0/orbit1 are dummies). | |
time0 | Start time [Decimal days (Processing format)]. | |
time1 | Stop time [Decimal days (Processing format)]. | |
orbit0 | Start orbit. | |
orbit1 | Stop orbit. |
void EECFI::OrbitId::init | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
double | time, | |||
long | orbit0, | |||
long | driftMode, | |||
double | ascMlstDrift, | |||
double | inclination, | |||
long | irep, | |||
long | icyc, | |||
double | rlong, | |||
double | ascMlst | |||
) | throw (CfiError) |
Initialise the orbit using orbital parameters.
This method is deprecated. Use the one that uses a RefOrbitInfo object to introduce orbital parameters.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum). | |
time | Reference time (Decimal days - Processing format). | |
orbit0 | Absolute orbit number of the reference orbit. | |
driftMode | Flag to select between mlst and inclination as input characterization of reference orbit. Allowed values:
. | |
ascMlstDrift | Drift in mlst of the reference orbit [seconds/day]. | |
inclination | Inclination of the reference orbit [deg]. Allowed range = [0, 180]. | |
irep | Repeat cycle of the reference orbit [days]. Allowed range: > 0. | |
icyc | Cycle length of the reference orbit [orbits]. Allowed range: > 0. | |
rlong | Geocentric longitude of the ascending node (EF RF) [deg]. Allowed range = [0, 360) | |
ascMlst | MLST at ascending node [Decimal hours]. Allowed range = [0, 24). |
void EECFI::OrbitId::init | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
double | time, | |||
double | pos[3], | |||
double | vel[3], | |||
long | absOrbit, | |||
const PropagPreciseConf & | preciseConf | |||
) | throw (CfiError) |
Initialise the orbit using state vector with numerical propagator.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum). | |
time | Time. | |
pos | Position vector [m]. | |
vel | Velocity vector [m/s]. | |
absOrbit | Absolute orbit. | |
preciseConf | Numerical propagator configuration. Allowed range for some members:
. |
void EECFI::OrbitId::init | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
double | time, | |||
double | pos[3], | |||
double | vel[3], | |||
long | absOrbit | |||
) | throw (CfiError) |
void EECFI::OrbitId::init | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
const vector< string > & | inputFiles, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1, | |||
const PropagPreciseConf & | preciseConf | |||
) | throw (CfiError) |
Initialise the orbit using orbit file with numerical propagator.
In order to read files, this method internally uses Data Handling functions. Please refer to [D_H_SUM] for further details.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
timeRef | Time reference (TimeRefOrbitEnum. When using DORIS Navigator files and time_mode is XOCFI_SEL_TIME, only XOCFI_TIME_UTC is allowed.). | |
orbitFileMode | Flag that indicates the type of the input orbit file (OrbitInitModeEnum ONLY PRECISE models).
. | |
inputFiles | Vector of orbit files. | |
timeInitMode | Flag for selecting the time range of the initialisation (XOCFI_SEL_FILE, XOCFI_SEL_TIME, XOCFI_SEL_ORBIT. For DORIS Navigator files, XOCFI_SEL_ORBIT is not allowed). For TLE files, the whole file is always selected (this flag and the parameters time0/time1, orbit0/orbit1 are dummies). | |
time0 | Start time [Decimal days (Processing format)]. | |
time1 | Stop time [Decimal days (Processing format)]. | |
orbit0 | Start orbit. | |
orbit1 | Stop orbit. | |
preciseConf | Numerical propagator configuration. Allowed range for some members:
. |
void EECFI::OrbitId::init | ( | const SatId & | satId, | |
const ModelId & | modelId, | |||
const TimeCorrelation & | timeCor, | |||
const GeoOrbitInitData & | geoOrbitInit | |||
) | throw (CfiError) |
Class constructor: intialization with geostationary satellite. The only input geodetic coordinate taken into account in initialization is the geocentric longitude; the latitude is set to 0. degrees and the altitude is set to 35786 km independently of the inputs.
satId | Satellite Id. | |
modelId | Model Id. | |
timeCor | Time correlations. | |
geoOrbitInit | Geostationary satellite initialization information. |
void EECFI::OrbitId::operator= | ( | const OrbitId & | orbitIdIn | ) |
Copy operator.
orbitIdIn | OrbitId we want to copy. |
References EECFI::CfiId::addInstance().
StateVector EECFI::OrbitId::osvCompute | ( | long | mode, | |
long | timeRef, | |||
double | time | |||
) | const throw (CfiError) |
Computes a satellite state vector for a given time.
Orbit initialisation mode | OSV computation method |
---|---|
XOCFI_ORBIT_INIT_ORBIT_CHANGE_MODE Initialised using an orbit definition |
Mean Keplerian Propagation Model with "AUTO" and "DOUBLE" modes. |
XOCFI_ORBIT_INIT_OSF_MODE XOCFI_ORBIT_INIT_OEF_OSF_MODE Initialised with an OSF file (or an OEF but reading the list of orbital changes in the data block of the file) |
|
XOCFI_ORBIT_INIT_POF_MODE XOCFI_ORBIT_INIT_OEF_POF_MODE Initialised with a POF file (or an OEF but reading the list of State Vectors in the data block of the file) |
|
XOCFI_ORBIT_INIT_STATE_VECTOR_MODE Initialised with an orbit state vector |
Mean Keplerian Propagation Model |
XOCFI_ORBIT_INIT_POF_N_DORIS_MODE: Initialised with a POF and a DORIS file |
|
XOCFI_ORBIT_INIT_TLE_MODE Initialised with a TLE file |
TLE propagation mode with "AUTO" mode |
XOCFI_ORBIT_INIT_POF_PRECISE_MODE XOCFI_ORBIT_INIT_OEF_POF_PRECISE_MODE Initialised with a POF file (or an OEF but reading the list of State Vectors in the data block of the file) |
Numerical propagator with "AUTO" mode |
XOCFI_ORBIT_INIT_ROF_PRECISE_MODE Initialised with xo_orbit_init_file_precise with a ROF file |
|
XOCFI_ORBIT_INIT_DORIS_PRECISE_MODE Initialised with xo_orbit_init_file_precise with a DORIS Navigator file |
|
XOCFI_ORBIT_INIT_STATE_VECTOR_PRECISE_MODE Initialised with xo_orbit_cart_init_precise |
Numerical propagator |
XOCFI_ORBIT_INIT_POF_N_DORIS_PRECISE_MODE Initialised with xo_orbit_init_file_precise with a POF and a DORIS Navigator file |
|
XOCFI_ORBIT_INIT_ROF_MODE Initialised with xo_orbit_init_file with a ROF file |
Interpolation |
XOCFI_ORBIT_INIT_DORIS_MODE Initialised with xo_orbit_init_file with a DORIS Navigator file |
mode | Propagation/interpolation mode (dummy for current version). | |
timeRef | Time reference (TimeRefOrbitEnum). | |
time | Time. |
StateVectorExtraInfo EECFI::OrbitId::osvComputeExtra | ( | long | extraChoice | ) | const throw (CfiError) |
Get orbital auxiliary data for the satellite state vector computed with osvCompute.
This software returns ancillary results derived from an orbit state vector obtained from the OrbitId::osvCompute routine (stored within the orbit Id). This state vector depends on which is the last function called:Orbit initialisation mode | OSV compute model |
---|---|
XOCFI_ORBIT_INIT_ORBIT_CHANGE_MODE XOCFI_ORBIT_INIT_OSF_MODE XOCFI_ORBIT_INIT_OEF_OSF_MODE XOCFI_ORBIT_INIT_POF_MODE XOCFI_ORBIT_INIT_OEF_POF_MODE XOCFI_ORBIT_INIT_STATE_VECTOR_MODE XOCFI_ORBIT_INIT_POF_N_DORIS_MODE |
Mean Kepler |
XOCFI_ORBIT_INIT_TLE_MODE | TLE |
XOCFI_ORBIT_INIT_POF_PRECISE_MODE XOCFI_ORBIT_INIT_OEF_POF_PRECISE_MODE XOCFI_ORBIT_INIT_ROF_PRECISE_MODE XOCFI_ORBIT_INIT_DORIS_PRECISE_MODE XOCFI_ORBIT_INIT_STATE_VECTOR_PRECISE_MODE XOCFI_ORBIT_INIT_POF_N_DORIS_PRECISE_MODE |
Precise |
XOCFI_ORBIT_INIT_ROF_MODE XOCFI_ORBIT_INIT_DORIS_MODE |
Interpolation |
Result parameter | Set | Description (Reference) | Unit (Format) | Allowed Range | OSV compute model |
[0] XOCFI_ORBIT_EXTRA_DEP_NODAL_PERIOD |
ANX Timing | Nodal period | s | >= 0 |
|
[1] XOCFI_ORBIT_EXTRA_DEP_UTC_CURRENT_ANX |
Time of current ANX | decimal days (Processing format) | - | ||
[2] XOCFI_ORBIT_EXTRA_DEP_ORBIT_NUMBER |
Position in orbit | Absolute Orbit Number | - | > 0 |
|
[3] XOCFI_ORBIT_EXTRA_DEP_SEC_SINCE_ANX |
Time since ANX | s | >= 0 < Nodal Period |
||
[4:9] XOCFI_ORBIT_EXTRA_DEP_MEAN_KEPL_A XOCFI_ORBIT_EXTRA_DEP_MEAN_KEPL_E XOCFI_ORBIT_EXTRA_DEP_MEAN_KEPL_I XOCFI_ORBIT_EXTRA_DEP_MEAN_KEPL_RA XOCFI_ORBIT_EXTRA_DEP_MEAN_KEPL_W XOCFI_ORBIT_EXTRA_DEP_MEAN_KEPL_M |
Mean Kepler | Mean Kepler elements of the propagated OSV (True of Date) | - | - |
|
Result parameter (res element) | Set | Description (Reference) | Unit (Format) | Allowed Range |
---|---|---|---|---|
[0] XOCFI_ORBIT_EXTRA_GEOC_LONG |
Geolocation | Geocentric longitude of satellite and SSP (EF frame) | deg | >= 0 < 360 |
[1] XOCFI_ORBIT_EXTRA_GEOD_LAT |
Geodetic latitude of satellite and SSP (EF frame) | deg | >= -90 <= +90 |
|
[2] XOCFI_ORBIT_EXTRA_GEOD_ALT |
Geodetic altitude of the satellite (EF frame) | m | - | |
[3] XOCFI_ORBIT_EXTRA_GEOC_LONG_D |
Geolocation rate | Geocentric longitude rate of satellite and SSP (EF frame) | deg/s | - |
[4] XOCFI_ORBIT_EXTRA_GEOD_LAT_D |
Geodetic latitude rate of satellite and SSP (EF frame) | deg/s | - | |
[5] XOCFI_ORBIT_EXTRA_GEOD_ALT_D |
Geodetic altitude rate of the satellite (EF frame) | m/s | - | |
[6] XOCFI_ORBIT_EXTRA_GEOC_LONG_2D |
Geolocation rate rate | Geocentric longitude rate-rate of satellite and SSP (EF frame) | deg/s2 | - |
[7] XOCFI_ORBIT_EXTRA_GEOD_LAT_2D |
Geodetic latitude rate-rate of satellite and SSP (EF frame) | deg/s2 | - | |
[8] XOCFI_ORBIT_EXTRA_GEOD_ALT_2D |
Geodetic altitude rate-rate of the satellite (EF frame) | m/s2 | - | |
[9] XOCFI_ORBIT_EXTRA_RAD_CUR_PARALLEL_MERIDIAN |
Geolocation extra | Radius of curvature parallel to meridian at the SSP (EF frame) | m | >= 0 |
[10] XOCFI_ORBIT_EXTRA_RAD_CUR_ORTHO_MERIDIAN |
Radius of curvature orthogonal to meridian at the SSP (EF frame) | m | >= 0 | |
[11] XOCFI_ORBIT_EXTRA_RAD_CUR_ALONG_GROUNDTRACK |
Radius of curvature along groundtrack at the SSP (EF frame) | m | >= 0 | |
[12] XOCFI_ORBIT_EXTRA_NORTH_VEL |
Earth-fixed velocity | Northward component of the velocity relative to the Earth of the SSP (Topocentric frame) | m/s | - |
[13] XOCFI_ORBIT_EXTRA_EAST_VEL |
Eastward component of the velocity relative to the Earth of the SSP (Topocentric frame) | m/s | - | |
[14] XOCFI_ORBIT_EXTRA_MAG_VEL |
Magnitude of the velocity relative to the Earth of the SSP (Topocentric frame) | m/s | >= 0 | |
[15] XOCFI_ORBIT_EXTRA_AZ_VEL |
Azimuth of the velocity relative to the Earth of the SSP (Topocentric frame) | deg | >= 0 < 360 |
|
[16] XOCFI_ORBIT_EXTRA_NORTH_ACC |
Earth-fixed acceleration | Northward component of the acceleration relative to the Earth of the SSP (Topocentric frame) | m/s2 | - |
[17] XOCFI_ORBIT_EXTRA_EAST_ACC |
Eastward component of the acceleration relative to the Earth of the SSP (Topocentric frame) | m/s2 | - | |
[18] XOCFI_ORBIT_EXTRA_GROUNDTRACK_TANG_ACC |
Groundtrack tangential component of the acceleration relative to the Earth of the SSP (Topocentric frame) | m/s2 | - | |
[19] XOCFI_ORBIT_EXTRA_AZ_ACC |
Azimuth of the acceleration relative to the Earth of the SSP (Topocentric frame) | deg | >= 0 < 360 |
|
[20] XOCFI_ORBIT_EXTRA_SAT_ECLIPSE_FLAG |
Sun | Satellite eclipse flag 0 = No 1 = Yes |
- | 0, 1 |
[21] XOCFI_ORBIT_EXTRA_SZA |
Sun Zenith Angle | deg | >= 0 < 180 |
|
[22] XOCFI_ORBIT_EXTRA_MLST |
Mean local solar time at the SSP | decimal hour | >= 0 < 24 |
|
[23] XOCFI_ORBIT_EXTRA_TLST |
True local solar time at the SSP | decimal hour | >= 0 < 24 |
|
[24] XOCFI_ORBIT_EXTRA_TRUE_SUN_RA |
True Sun’s (centre) right ascension (TOD frame) | deg | >= 0 < 360 |
|
[25] XOCFI_ORBIT_EXTRA_TRUE_SUN_DEC |
True Sun’s (centre) declination (TOD frame) | deg | >= -90 <= +90 |
|
[26] XOCFI_ORBIT_EXTRA_TRUE_SUN_SEMI_DIAM |
True Sun’s semi-diameter | deg | >= 0 | |
[27] XOCFI_ORBIT_EXTRA_MOON_RA |
Moon | Moon’s (centre) right ascension (TOD frame) | deg | >= 0 < 360 |
[28] XOCFI_ORBIT_EXTRA_MOON_DEC |
Moon’s (centre) declination (TOD frame) | deg | >= -90 <= +90 |
|
[29] XOCFI_ORBIT_EXTRA_MOON_SEMI_DIAM |
Moon’s semi-diameter | deg | >= 0 | |
[30] XOCFI_ORBIT_EXTRA_MOON_AREA_LIT |
Area of Moon lit by Sun | - | >= 0 <= 1 |
|
[31:36] XOCFI_ORBIT_EXTRA_OSC_KEPL_A XOCFI_ORBIT_EXTRA_OSC_KEPL_E XOCFI_ORBIT_EXTRA_OSC_KEPL_I XOCFI_ORBIT_EXTRA_OSC_KEPL_RA XOCFI_ORBIT_EXTRA_OSC_KEPL_W XOCFI_ORBIT_EXTRA_OSC_KEPL_M |
Osculating Kepler | Osculating Keplerian elements of the OSV (TOD frame) | - | - |
[37] XOCFI_ORBIT_EXTRA_ORBIT_RAD |
Inertial Aux | Orbit radius (TOD frame) | m | >= 0 |
[38] XOCFI_ORBIT_EXTRA_RADIAL_ORB_VEL |
Radial orbit velocity component (TOD frame) | m/s | - | |
[39] XOCFI_ORBIT_EXTRA_TRANS_ORB_VEL |
Transversal orbit velocity component (TOD frame) | m/s | - | |
[40] XOCFI_ORBIT_EXTRA_ORB_VEL_MAG |
Orbit velocity magnitude (TOD frame) | m/s | >= 0 | |
[41] XOCFI_ORBIT_EXTRA_RA_SAT |
Right ascension of the satellite (TOD frame) | deg | >= 0 < 360 |
|
[42] XOCFI_ORBIT_EXTRA_DEC_SAT |
Declination of the satellite (TOD frame) | deg | >= -90 <= +90 |
|
[43] XOCFI_ORBIT_EXTRA_EARTH_ROTATION_ANGLE |
Earth rotation angle [H] | deg | >= 0 < 360 |
|
[44] XOCFI_ORBIT_EXTRA_RA_SAT_D |
Right ascension rate of the satellite (TOD frame) | deg/s | - | |
[45] XOCFI_ORBIT_EXTRA_RA_SAT_2D |
Right ascension rate-rate of the satellite (TOD frame) | deg/s2 | - | |
[46] XOCFI_ORBIT_EXTRA_OSC_TRUE_LAT |
Satellite osculating true latitude (EF frame) | deg | >= 0 < 360 |
|
[47] XOCFI_ORBIT_EXTRA_OSC_TRUE_LAT_D |
Satellite osculating true latitude rate (EF frame) | deg/s | - | |
[48] XOCFI_ORBIT_EXTRA_OSC_TRUE_LAT_2D |
Satellite osculating true latitude rate-rate (EF frame) | deg/s2 | - |
extraChoice | Flag to select the type of extra information (OrbitExtraChoiceEnum). |
References EECFI::StateVectorExtraInfo::modelDep, and EECFI::StateVectorExtraInfo::modelIndep.
TleRec EECFI::OrbitId::osvToTle | ( | long | timeMode, | |
long | timeRef, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throw (CfiError) |
Generates a TLE by fitting the set of orbit state vectors stored in the orbit_id.
This set of OSVs are selected from the input orbit_id for the orbit/time requested range in the following way:
timeMode | Time/orbit selection (XOCFI_SEL_TIME, XOCFI_SEL_ORBIT or XOCFI_SEL_DEFAULT). For the XOCFI_SEL_DEFAULT mode, the whole range of orbits stored in the orbitId is selected. | |
timeRef | Time reference (TimeRefOrbitEnum). Only used if timeMode is XOCFI_SEL_FILE. | |
time0 | Start time [days]. | |
time1 | Stop time [days]. | |
orbit0 | Start orbit. | |
orbit1 | Stop orbit. |
StateVector EECFI::OrbitId::positionOnOrbitToTime | ( | long | abs_orbit_number, | |
long | angle_type, | |||
double | angle, | |||
double | angle_rate, | |||
double | angle_rate_rate, | |||
long | deriv, | |||
long | time_ref | |||
) | const throw (CfiError) |
Calculates the time, position and velocity vectors in Earth-Fixed associated to a given position on orbit.
This position on orbit is defined as the angle between the satellite position and the intersection of the orbital plane with a reference plane (the reference plane is the equator in GM2000, ToD or EF CS).
abs_orbit_number | Absolute orbit number | |
angle_type | Angle type | |
angle | Angle describing the position in the orbit | |
angle_rate | Orbit rate > 1st derivate from Angle | |
angle_rate_rate | Orbit rate rate > 2nd derivate from Angle | |
deriv | Derivative ID | |
time_ref | Time Reference |
SatId EECFI::OrbitId::satId | ( | ) | const |
Return satellite id.
void EECFI::OrbitId::setAnx | ( | const vector< ANXExtra > & | anxList | ) |
Sets the list of ANX data stored in the OrbitId object.
anxList | List of ANX info. |
References EECFI::CfiError::addMsg(), and EECFI::CfiClass::throwWarn.
void EECFI::OrbitId::setGeoOrbitInfo | ( | const GeoOrbitInfo & | geoOrbitInfo | ) | throw (CfiError) |
Set geostationary satellite information.
geoOrbitInfo | Geostationary orbit information. |
References EECFI::CfiError::addMsg().
void EECFI::OrbitId::setOsf | ( | const vector< OsfRecords > & | osfRecList | ) |
Sets the list of orbital changes stored in the OrbitId object.
osfRecList | List of orbit changes. |
References EECFI::CfiError::addMsg(), and EECFI::CfiClass::throwWarn.
void EECFI::OrbitId::setOsv | ( | const vector< OsvRec > & | osvRecList | ) |
Sets the list of orbit state vectors stored in the OrbitId object.
osvRecList | List of orbit state vectors. |
References EECFI::CfiError::addMsg(), and EECFI::CfiClass::throwWarn.
void EECFI::OrbitId::setPrecisePropagConfig | ( | const PropagPreciseConf & | preciseConf | ) |
Set numerical propagator configuration.
preciseConf | Numerical propagator configuration. |
References EECFI::CfiError::addMsg(), EECFI::PropagPreciseConf::ap, EECFI::PropagPreciseConf::atmosFlag, EECFI::PropagPreciseConf::f107, EECFI::PropagPreciseConf::f107a, EECFI::PropagPreciseConf::gravDegree, EECFI::PropagPreciseConf::gravFile, EECFI::PropagPreciseConf::gravityFlag, EECFI::PropagPreciseConf::gravOrder, EECFI::PropagPreciseConf::modelsPath, EECFI::PropagPreciseConf::scDragArea, EECFI::PropagPreciseConf::scDragCoeff, EECFI::PropagPreciseConf::scMass, EECFI::PropagPreciseConf::scSrpArea, EECFI::PropagPreciseConf::scSrpCoeff, EECFI::PropagPreciseConf::sgaApFile, EECFI::PropagPreciseConf::sgaF107File, EECFI::PropagPreciseConf::sgaFlag, EECFI::PropagPreciseConf::srpFlag, EECFI::PropagPreciseConf::step, EECFI::PropagPreciseConf::thirdbodyFlag, EECFI::CfiClass::throwWarn, and EECFI::PropagPreciseConf::userFlag.
void EECFI::OrbitId::setValTime | ( | const ValidityTime & | valTime | ) |
Sets validity times.
valTime | Validity times. |
References EECFI::CfiError::addMsg(), EECFI::ValidityTime::start, EECFI::ValidityTime::stop, EECFI::CfiClass::throwWarn, and EECFI::ValidityTime::timeRef.