public interface LOF
Modifier and Type | Method and Description |
---|---|
String |
getName()
Get name of the local orbital frame.
|
default boolean |
isQuasiInertial()
Get flag that indicates if current local orbital frame shall be treated as pseudo-inertial.
|
org.hipparchus.geometry.euclidean.threed.Rotation |
rotationFromInertial(AbsoluteDate date,
PVCoordinates pv)
Get the rotation from inertial frame to local orbital frame.
|
<T extends org.hipparchus.CalculusFieldElement<T>> |
rotationFromInertial(org.hipparchus.Field<T> field,
FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pv)
Get the rotation from inertial frame to local orbital frame.
|
default <T extends org.hipparchus.CalculusFieldElement<T>> |
rotationFromLOF(org.hipparchus.Field<T> field,
LOF fromLOF,
FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pv)
Get the rotation from input
local orbital frame to the instance. |
default org.hipparchus.geometry.euclidean.threed.Rotation |
rotationFromLOF(LOF fromLOF,
AbsoluteDate date,
PVCoordinates pv)
Get the rotation from input
local orbital frame to the instance. |
static <T extends org.hipparchus.CalculusFieldElement<T>> |
rotationFromLOFInToLOFOut(org.hipparchus.Field<T> field,
LOF in,
LOF out,
FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pv)
Get the rotation from input to output
local orbital frame . |
static org.hipparchus.geometry.euclidean.threed.Rotation |
rotationFromLOFInToLOFOut(LOF in,
LOF out,
AbsoluteDate date,
PVCoordinates pv)
Get the rotation from input to output
local orbital frame . |
default Transform |
transformFromInertial(AbsoluteDate date,
PVCoordinates pv)
Get the transform from an inertial frame defining position-velocity and the local orbital frame.
|
default <T extends org.hipparchus.CalculusFieldElement<T>> |
transformFromInertial(FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pv)
Get the transform from an inertial frame defining position-velocity and the local orbital frame.
|
default Transform |
transformFromLOF(LOF fromLOF,
AbsoluteDate date,
PVCoordinates pv)
Get the rotation from input
local orbital frame to the instance. |
default <T extends org.hipparchus.CalculusFieldElement<T>> |
transformFromLOF(LOF fromLOF,
FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pv)
Get the rotation from input
commonly used local orbital frame to the instance. |
static Transform |
transformFromLOFInToLOFOut(LOF in,
LOF out,
AbsoluteDate date,
PVCoordinates pv)
Get the transform from input to output
local orbital frame . |
static <T extends org.hipparchus.CalculusFieldElement<T>> |
transformFromLOFInToLOFOut(LOF in,
LOF out,
FieldAbsoluteDate<T> date,
FieldPVCoordinates<T> pv)
Get the transform from input to output
local orbital frame . |
static <T extends org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotationFromLOFInToLOFOut(org.hipparchus.Field<T> field, LOF in, LOF out, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pv)
local orbital frame
.
This rotation does not include any time derivatives. If first time derivatives (i.e. rotation rate) is needed as well,
the full transformFromLOFInToLOFOut(LOF, LOF, FieldAbsoluteDate, FieldPVCoordinates)
method must be called and
the complete rotation transform must be extracted from it.
T
- type of the field elementsfield
- field to which the elements belongin
- input commonly used local orbital frameout
- output commonly used local orbital framedate
- date of the rotationpv
- position-velocity of the spacecraft in some inertial framestatic <T extends org.hipparchus.CalculusFieldElement<T>> FieldTransform<T> transformFromLOFInToLOFOut(LOF in, LOF out, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pv)
local orbital frame
.T
- type of the field elementsin
- input commonly used local orbital frameout
- output commonly used local orbital framedate
- date of the transformpv
- position-velocity of the spacecraft in some inertial framestatic org.hipparchus.geometry.euclidean.threed.Rotation rotationFromLOFInToLOFOut(LOF in, LOF out, AbsoluteDate date, PVCoordinates pv)
local orbital frame
.
This rotation does not include any time derivatives. If first time derivatives (i.e. rotation rate) is needed as well,
the full transformFromLOFInToLOFOut(LOF, LOF, AbsoluteDate, PVCoordinates)
method must be called and
the complete rotation transform must be extracted from it.
in
- input commonly used local orbital frameout
- output commonly used local orbital framedate
- date of the rotationpv
- position-velocity of the spacecraft in some inertial framestatic Transform transformFromLOFInToLOFOut(LOF in, LOF out, AbsoluteDate date, PVCoordinates pv)
local orbital frame
.in
- input commonly used local orbital frameout
- output commonly used local orbital framedate
- date of the transformpv
- position-velocity of the spacecraft in some inertial framedefault <T extends org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotationFromLOF(org.hipparchus.Field<T> field, LOF fromLOF, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pv)
local orbital frame
to the instance.
This rotation does not include any time derivatives. If first time derivatives (i.e. rotation rate) is needed as well,
the full transformFromLOF(LOF, FieldAbsoluteDate, FieldPVCoordinates)
method must be called and
the complete rotation transform must be extracted from it.
T
- type of the field elementsfield
- field to which the elements belongfromLOF
- input local orbital framedate
- date of the rotationpv
- position-velocity of the spacecraft in some inertial framedefault <T extends org.hipparchus.CalculusFieldElement<T>> FieldTransform<T> transformFromLOF(LOF fromLOF, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pv)
commonly used local orbital frame
to the instance.T
- type of the field elementsfromLOF
- input local orbital framedate
- date of the transformpv
- position-velocity of the spacecraft in some inertial framedefault <T extends org.hipparchus.CalculusFieldElement<T>> FieldTransform<T> transformFromInertial(FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pv)
T
- type of the fields elementsdate
- current datepv
- position-velocity of the spacecraft in some inertial frame<T extends org.hipparchus.CalculusFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotationFromInertial(org.hipparchus.Field<T> field, FieldAbsoluteDate<T> date, FieldPVCoordinates<T> pv)
This rotation does not include any time derivatives. If first time derivatives (i.e. rotation rate) is needed as well,
the full transformFromInertial(FieldAbsoluteDate, FieldPVCoordinates)
method must be
called and the complete rotation transform must be extracted from it.
T
- type of the field elementsfield
- field to which the elements belongdate
- date of the rotationpv
- position-velocity of the spacecraft in some inertial framedefault org.hipparchus.geometry.euclidean.threed.Rotation rotationFromLOF(LOF fromLOF, AbsoluteDate date, PVCoordinates pv)
local orbital frame
to the instance.
This rotation does not include any time derivatives. If first time derivatives (i.e. rotation rate) is needed as well,
the full transformFromLOF(LOF, AbsoluteDate, PVCoordinates)
method must be called and
the complete rotation transform must be extracted from it.
fromLOF
- input local orbital framedate
- date of the rotationpv
- position-velocity of the spacecraft in some inertial framedefault Transform transformFromLOF(LOF fromLOF, AbsoluteDate date, PVCoordinates pv)
local orbital frame
to the instance.fromLOF
- input local orbital framedate
- date of the transformpv
- position-velocity of the spacecraft in some inertial framedefault Transform transformFromInertial(AbsoluteDate date, PVCoordinates pv)
date
- current datepv
- position-velocity of the spacecraft in some inertial frameorg.hipparchus.geometry.euclidean.threed.Rotation rotationFromInertial(AbsoluteDate date, PVCoordinates pv)
This rotation does not include any time derivatives. If first time derivatives (i.e. rotation rate) is needed as well,
the full transformFromInertial
method must be called and
the complete rotation transform must be extracted from it.
date
- date of the rotationpv
- position-velocity of the spacecraft in some inertial framedefault boolean isQuasiInertial()
String getName()
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