Earth Observation Mission CFI Software Lib Software User Manual for JAVA |
Base class for StateVector objects. More...
Public Member Functions | |
StateVector () | |
Class constructor (empty constructor). | |
StateVector (Time timeIn, Coord coordIn) | |
Class constructor. | |
native StateVector | change (ModelId modelId, long deriv, long newCS) throws CfiError |
Change coordinate system. | |
native void | setSun (ModelId modelId, Time time) throws CfiError |
Set Sun state vector. | |
native void | setMoon (ModelId modelId, Time time) throws CfiError |
Set Moon state vector. | |
native void | setPlanet (ModelId modelId, Time time, long planet) throws CfiError |
Set state vector for the requested planet. | |
native OrbitPos | getPositionOnOrbit (ModelId modelId, long angleType, long deriv) throws CfiError |
Get the true latitude corresponding to the state vector. | |
Public Attributes | |
Time | time |
Time object. | |
Coord | coord |
Coordinates. |
Base class for StateVector objects.
EECFI.StateVector.StateVector | ( | ) |
Class constructor (empty constructor).
Class constructor.
time | Time of the state vector. | |
coord | Coordinates. |
StateVector EECFI.StateVector::change | ( | ModelId | modelId, | |
long | deriv, | |||
long | newCS | |||
) | throws CfiError |
Change coordinate system.
This method transforms a cartesian state vector between different reference frames. The transformation are done sequentially following the schema in next figure:
. Time attribute Time must have time correlations initialized. Note that the transformations between BM2000, HM2000 and GM2000 involve a translation of the input vectors (TR3 and TR3’). In case that the input vector is a direction and not a location, the transformation should only apply the rotations between frames, so the transformation should be done in several steps with StateVector.change, skipping the translations.
Permitted CS = XLCFI_CS_GALACTIC, XLCFI_CS_BM1950, XLCFI_CS_BM2000, XLCFI_CS_HM2000, XLCFI_CS_GM2000, XLCFI_CS_MOD, XLCFI_CS_TOD or XLCFI_CS_EF.
modelId | Model Id. | |
deriv | derivative to be computed (XLCFI_NO_DER or XLCFI_1ST_DER). | |
newCS | New coordinate frame (CoordinateSystemEnum). |
OrbitPos EECFI.StateVector::getPositionOnOrbit | ( | ModelId | modelId, | |
long | angleType, | |||
long | deriv | |||
) | throws CfiError |
Get the true latitude corresponding to the state vector.
Get the true/mean latitude describing the position on the orbit. The latitude angle is the angle between the satellite position and the intersection of the orbital plane with a given reference plane. Asumption: the state vector is given in EF.
modelId | Model Id. | |
angleType | Type of angle(AngleTypeEnum). It defines the reference plane. (Note: XLCFI_ANGLE_TYPE_MEAN_LAT_TOD is not supported) | |
deriv | Derivative (DerivEnum). |
Set Moon state vector.
It is computed the position and velocity in EF CS.
modelId | Model id. | |
time | Requested time. |
Set state vector for the requested planet.
It is computed the position and velocity in EF CS.
modelId | Model id. | |
time | requested time. | |
planet | (PlanetEnum). |
Set Sun state vector.
It is computed the position and velocity in EF CS.
modelId | Model id. | |
time | Requested time. |
Coordinates.
Time object.