DEIMOS
Earth Observation Mission CFI Software
Lib Software User Manual
for JAVA		 ESA
Public Member Functions | Public Attributes

EECFI.StateVector Class Reference

Base class for StateVector objects. More...

Inheritance diagram for EECFI.StateVector:
EECFI.CfiClass

List of all members.

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.

Detailed Description

Base class for StateVector objects.

Constructor & Destructor Documentation

EECFI.StateVector.StateVector (  ) 

Class constructor (empty constructor).

EECFI.StateVector::StateVector ( Time  time,
Coord  coord 
)

Class constructor.

Parameters:
time Time of the state vector.
coord Coordinates.

Member Function Documentation

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:

change_coord.jpg

. 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.

Parameters:
modelId Model Id.
deriv derivative to be computed (XLCFI_NO_DER or XLCFI_1ST_DER).
newCS New coordinate frame (CoordinateSystemEnum).
Returns:
State vector in new reference system.
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.

Parameters:
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).
void EECFI.StateVector::setMoon ( ModelId  modelId,
Time  time 
) throws CfiError

Set Moon state vector.

It is computed the position and velocity in EF CS.

Parameters:
modelId Model id.
time Requested time.
void EECFI.StateVector::setPlanet ( ModelId  modelId,
Time  time,
long  planet 
) throws CfiError

Set state vector for the requested planet.

It is computed the position and velocity in EF CS.

Parameters:
modelId Model id.
time requested time.
planet (PlanetEnum).
void EECFI.StateVector::setSun ( ModelId  modelId,
Time  time 
) throws CfiError

Set Sun state vector.

It is computed the position and velocity in EF CS.

Parameters:
modelId Model id.
time Requested time.

Member Data Documentation

Coord EECFI.StateVector.coord

Coordinates.

Time EECFI.StateVector.time

Time object.

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