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Earth Observation Mission CFI Software Orbit Software User Manual for JAVA |
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Class that stores the orbit data. More...
Public Member Functions | |
OrbitId (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, double time, long orbit0, long driftMode, double ascMlstDrift, double inclination, long irep, long icyc, double rlong, double ascMlst) throws CfiError | |
Class constructor: using orbital parameters. | |
OrbitId (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, double time, long orbit0, final RefOrbitInfo refOrbitInfo) throws CfiError | |
Class constructor: using orbital parameters with support for MLST non linear drift. | |
OrbitId (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, double time, double[] pos, double[] vel, long absOrbit) throws CfiError | |
Class constructor: using state Vector. | |
OrbitId (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, long orbitFileMode, final Vector< String > inputFiles, long timeInitMode, double time0, double time1, long orbit0, long orbit1) throws CfiError | |
Class constructor: using orbit file. | |
OrbitId (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, double time, double[] pos, double[] vel, long absOrbit, final PropagPreciseConf preciseConf) throws CfiError | |
Class constructor: numerical propagator using state Vector. | |
OrbitId (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, long orbitFileMode, final Vector< String > inputFiles, long timeInitMode, double time0, double time1, long orbit0, long orbit1, final PropagPreciseConf preciseConf) throws CfiError | |
Class constructor: numerical propagator using orbit file. | |
OrbitId (OrbitId orbitIdIn) throws CfiError | |
Copy constructor. | |
native void | init (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, double time, long orbit0, long driftMode, double ascMlstDrift, double inclination, long irep, long icyc, double rlong, double ascMlst) throws CfiError |
Initialise the orbit using orbital parameters. | |
native void | init (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, double time, long orbit0, final RefOrbitInfo refOrbitInfo) throws CfiError |
Class constructor: using orbital parameters with support for MLST non linear drift. | |
native void | init (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, double time, double[] pos, double[] vel, long absOrbit) throws CfiError |
Initialise the orbit using state Vector. | |
native void | init (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, long orbitFileMode, final Vector< String > inputFiles, long timeInitMode, double time0, double time1, long orbit0, long orbit1) throws CfiError |
Initialise the orbit using orbit file. | |
native void | init (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, double time, double[] pos, double[] vel, long absOrbit, final PropagPreciseConf preciseConf) throws CfiError |
Initialise the orbit using state Vector with numerical propagator. | |
native void | init (final SatId satId, final ModelId modelId, final TimeCorrelation timeCor, long timeRef, long orbitFileMode, final Vector< String > inputFiles, long timeInitMode, double time0, double time1, long orbit0, long orbit1, final PropagPreciseConf preciseConf) throws CfiError |
Initialise the orbit using orbit file with numerical propagator. | |
native SatId | satId () |
Return satellite id. | |
native Vector< OsvRec > | getOsv () |
Returns the list of orbit state Vectors stored in the OrbitId object. | |
native void | setOsv (final Vector< OsvRec > osvRecList) |
Sets the list of orbit state Vectors stored in the OrbitId object. | |
native Vector< ANXExtra > | getAnx () |
Returns the list of ANX data stored in the OrbitId object. | |
native void | setAnx (final Vector< ANXExtra > anxList) |
Sets the list of ANX data stored in the OrbitId object. | |
native Vector< OsfRecords > | getOsf () |
Returns the list of orbital changes stored in the OrbitId object. | |
native void | setOsf (final Vector< OsfRecords > osvRecList) |
Sets the list of orbital changes stored in the OrbitId object. | |
native ValidityTime | getValTime () |
Returns validity times. | |
native void | setValTime (final ValidityTime valTime) |
Sets validity times. | |
native PropagPreciseConf | getPrecisePropagConfig () throws CfiError |
Get numerical propagator configuration. | |
native void | setPrecisePropagConfig (final PropagPreciseConf preciseConf) |
Set numerical propagator configuration. | |
native OrbitalInfo | getOrbitInfo (long absoluteOrbit) throws CfiError |
Returns orbital information for a requested orbit. | |
native OrbitInfo | getOrbitNumbersFromRel (long relOrbit, long cycle) throws CfiError |
Gets orbit absolute orbit and phase number from the relative orbit. | |
native OrbitInfo | getOrbitNumbersFromPhase (long phase) throws CfiError |
Gets orbit absolute and relative orbit from the input phase number. | |
native OrbitInfo | getOrbitNumbersFromAbs (long absOrbit) throws CfiError |
Gets orbit relative orbit and phase from the input phase number. | |
native StateVector | osvCompute (long mode, long timeRef, double time) throws CfiError |
Computes a satellite state vector for a given time. | |
native StateVectorExtraInfo | osvComputeExtra (long extraChoice) throws CfiError |
Get orbital auxiliary data for the satellite state vector computed with osvCompute. | |
native TleRec | osvToTle (long timeMode, long timeRef, double time0, double time1, long orbit0, long orbit1) throws CfiError |
Generate a TLE by fitting the set of orbit state Vectors stored in the OrbitId. | |
void | eq (final OrbitId orbitIdIn) throws CfiError |
Copy operator. It overwrites the operator in CfiId to copy also TimeCorrelation member. |
Class that stores the orbit data.
EECFI.OrbitId::OrbitId | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
double | time, | |||
long | orbit0, | |||
long | driftMode, | |||
double | ascMlstDrift, | |||
double | inclination, | |||
long | irep, | |||
long | icyc, | |||
double | rlong, | |||
double | ascMlst | |||
) | throws CfiError |
Class constructor: 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). |
EECFI.OrbitId::OrbitId | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
double | time, | |||
long | orbit0, | |||
final RefOrbitInfo | refOrbitInfo | |||
) | throws CfiError |
Class constructor: using orbital parameters with support for MLST non linear drift.
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. | |
refOrbitInfo | Orbital parameters, with support for MLST non linear drift. |
EECFI.OrbitId::OrbitId | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
double | time, | |||
double[] | pos, | |||
double[] | vel, | |||
long | absOrbit | |||
) | throws CfiError |
EECFI.OrbitId::OrbitId | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
final Vector< String > | inputFiles, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throws CfiError |
Class constructor: using orbit file.
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 | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
double | time, | |||
double[] | pos, | |||
double[] | vel, | |||
long | absOrbit, | |||
final PropagPreciseConf | preciseConf | |||
) | throws 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 | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
final Vector< String > | inputFiles, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1, | |||
final PropagPreciseConf | preciseConf | |||
) | throws CfiError |
Class constructor: numerical propagator using orbit file.
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:
. |
Copy constructor.
orbitIdIn | Orbit Id to be copied. |
Copy operator. It overwrites the operator in CfiId to copy also TimeCorrelation member.
orbitIdIn | OrbitId we want to copy. |
Vector< ANXExtra > EECFI.OrbitId::getAnx | ( | ) |
Returns the list of ANX data stored in the OrbitId object.
OrbitalInfo EECFI.OrbitId::getOrbitInfo | ( | long | absoluteOrbit | ) | throws CfiError |
Returns orbital information for a requested orbit.
absoluteOrbit | Absolute orbit |
Gets orbit relative orbit and phase from the input phase number.
absOrbit | Absolute orbit. |
Gets orbit absolute and relative orbit from the input phase number.
phase | Phase of orbit. |
Gets orbit absolute orbit and phase number from the relative orbit.
relOrbit | Relative orbit | |
cycle | Cycle of orbit. |
Vector< OsfRecords > EECFI.OrbitId::getOsf | ( | ) |
Returns the list of orbital changes stored in the OrbitId object.
Vector< OsvRec > EECFI.OrbitId::getOsv | ( | ) |
Returns the list of orbit state Vectors stored in the OrbitId object.
PropagPreciseConf EECFI.OrbitId::getPrecisePropagConfig | ( | ) | throws CfiError |
Get numerical propagator configuration.
ValidityTime EECFI.OrbitId::getValTime | ( | ) |
Returns validity times.
void EECFI.OrbitId::init | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
double | time, | |||
long | orbit0, | |||
final RefOrbitInfo | refOrbitInfo | |||
) | throws CfiError |
Class constructor: using orbital parameters with support for MLST non linear drift.
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. | |
refOrbitInfo | Orbital parameters, including support for MLST non linear drift. |
void EECFI.OrbitId::init | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
final Vector< String > | inputFiles, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1, | |||
final PropagPreciseConf | preciseConf | |||
) | throws CfiError |
Initialise the orbit using orbit file with numerical propagator.
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 | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
double | time, | |||
double[] | pos, | |||
double[] | vel, | |||
long | absOrbit | |||
) | throws CfiError |
void EECFI.OrbitId::init | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
double | time, | |||
long | orbit0, | |||
long | driftMode, | |||
double | ascMlstDrift, | |||
double | inclination, | |||
long | irep, | |||
long | icyc, | |||
double | rlong, | |||
double | ascMlst | |||
) | throws 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 | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
double | time, | |||
double[] | pos, | |||
double[] | vel, | |||
long | absOrbit, | |||
final PropagPreciseConf | preciseConf | |||
) | throws 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 | ( | final SatId | satId, | |
final ModelId | modelId, | |||
final TimeCorrelation | timeCor, | |||
long | timeRef, | |||
long | orbitFileMode, | |||
final Vector< String > | inputFiles, | |||
long | timeInitMode, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throws CfiError |
Initialise the orbit using orbit file.
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. |
StateVector EECFI.OrbitId::osvCompute | ( | long | mode, | |
long | timeRef, | |||
double | time | |||
) | throws 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 | ) | throws 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 (TOD frame) | deg | >= 0 < 360 |
|
[47] XOCFI_ORBIT_EXTRA_OSC_TRUE_LAT_D |
Satellite osculating true latitude rate (TOD frame) | deg/s | - | |
[48] XOCFI_ORBIT_EXTRA_OSC_TRUE_LAT_2D |
Satellite osculating true latitude rate-rate (TOD frame) | deg/s2 | - |
extraChoice | Flag to select the type of extra information (OrbitExtraChoiceEnum). |
TleRec EECFI.OrbitId::osvToTle | ( | long | timeMode, | |
long | timeRef, | |||
double | time0, | |||
double | time1, | |||
long | orbit0, | |||
long | orbit1 | |||
) | throws CfiError |
Generate a TLE by fitting the set of orbit state Vectors stored in the OrbitId.
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. |
SatId EECFI.OrbitId::satId | ( | ) |
Return satellite id.
void EECFI.OrbitId::setAnx | ( | final Vector< ANXExtra > | anxList | ) |
Sets the list of ANX data stored in the OrbitId object.
anxList | List of ANX info. |
void EECFI.OrbitId::setOsf | ( | final Vector< OsfRecords > | osfRecList | ) |
Sets the list of orbital changes stored in the OrbitId object.
osfRecList | List of orbit changes. |
void EECFI.OrbitId::setOsv | ( | final Vector< OsvRec > | osvRecList | ) |
Sets the list of orbit state Vectors stored in the OrbitId object.
osvRecList | List of orbit state vectors. |
void EECFI.OrbitId::setPrecisePropagConfig | ( | final PropagPreciseConf | preciseConf | ) |
Set numerical propagator configuration.
preciseConf | Numerical propagator configuration. |
void EECFI.OrbitId::setValTime | ( | final ValidityTime | valTime | ) |
Sets validity times.
valTime | Validity times. |