Package | Description |
---|---|
org.orekit.attitudes |
This package provides classes to represent simple attitudes.
|
org.orekit.bodies |
This package provides interface to represent the position and geometry of
space objects such as stars, planets or asteroids.
|
org.orekit.files.ccsds |
This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
|
org.orekit.files.general |
This package provides interfaces for orbit file representations and corresponding parsers.
|
org.orekit.frames |
This package provides classes to handle frames and transforms between them.
|
org.orekit.orbits |
This package provides classes to represent orbits.
|
org.orekit.propagation |
This package provides tools to propagate orbital states with different methods.
|
org.orekit.propagation.analytical | |
org.orekit.propagation.analytical.tle |
This package provides classes to read and extrapolate tle's.
|
org.orekit.propagation.integration | |
org.orekit.propagation.numerical | |
org.orekit.utils |
This package provides useful objects.
|
Modifier and Type | Method and Description |
---|---|
protected PVCoordinates |
GroundPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
protected PVCoordinates |
GroundPointingWrapper.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
protected PVCoordinates |
TargetPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
protected PVCoordinates |
BodyCenterPointing.getTargetPV(PVCoordinatesProvider pvProv,
AbsoluteDate date,
Frame frame)
Compute the target point position/velocity in specified frame.
|
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
JPLEphemeridesLoader.RawPVProvider.getRawPV(AbsoluteDate date)
Get the position-velocity at date.
|
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
OPMFile.getPVCoordinates()
Get the position/velocity coordinates contained in the OPM.
|
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
SatelliteTimeCoordinate.getCoordinate()
Returns the coordinate of this entry.
|
Modifier and Type | Method and Description |
---|---|
void |
SatelliteTimeCoordinate.setCoordinate(PVCoordinates coordinate)
Set the coordinate for this entry.
|
Constructor and Description |
---|
SatelliteTimeCoordinate(AbsoluteDate time,
PVCoordinates coord)
Creates a new
SatelliteTimeCoordinate instance with
a given epoch and coordinate. |
SatelliteTimeCoordinate(AbsoluteDate time,
PVCoordinates coord,
double clockCorr,
double rateChange)
Creates a new
SatelliteTimeCoordinate instance with a given
epoch, coordinate and clock value / rate change. |
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
Transform.getCartesian()
Get the underlying elementary cartesian part.
|
PVCoordinates |
TopocentricFrame.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the topocentric frame origin in the selected frame. |
PVCoordinates |
SpacecraftFrame.getPVCoordinates(AbsoluteDate date,
Frame frame)
Deprecated.
Get the
PVCoordinates of the spacecraft frame origin in the selected frame. |
PVCoordinates |
Transform.transformPVCoordinates(PVCoordinates pv)
Transform
PVCoordinates including kinematic effects. |
Modifier and Type | Method and Description |
---|---|
double |
TopocentricFrame.getRangeRate(PVCoordinates extPV,
Frame frame,
AbsoluteDate date)
Get the range rate of a point with regards to the topocentric frame center point.
|
protected abstract Rotation |
LOFType.rotationFromInertial(PVCoordinates pv)
Get the rotation from inertial frame to local orbital frame.
|
Transform |
LOFType.transformFromInertial(AbsoluteDate date,
PVCoordinates pv)
Get the transform from an inertial frame defining position-velocity and the local orbital frame.
|
PVCoordinates |
Transform.transformPVCoordinates(PVCoordinates pv)
Transform
PVCoordinates including kinematic effects. |
Constructor and Description |
---|
Transform(AbsoluteDate date,
PVCoordinates cartesian)
Build a translation transform, with its first time derivative.
|
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
Orbit.getPVCoordinates()
Get the
PVCoordinates in definition frame. |
PVCoordinates |
Orbit.getPVCoordinates(AbsoluteDate otherDate,
Frame otherFrame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
Orbit.getPVCoordinates(Frame outputFrame)
Get the
PVCoordinates in a specified frame. |
protected abstract PVCoordinates |
Orbit.initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.
|
protected PVCoordinates |
CircularOrbit.initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.
|
protected PVCoordinates |
EquinoctialOrbit.initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.
|
protected PVCoordinates |
KeplerianOrbit.initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.
|
protected PVCoordinates |
CartesianOrbit.initPVCoordinates()
Compute the position/velocity coordinates from the canonical parameters.
|
Constructor and Description |
---|
CartesianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
CircularOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
EquinoctialOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
KeplerianOrbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Constructor from cartesian parameters.
|
Orbit(PVCoordinates pvCoordinates,
Frame frame,
AbsoluteDate date,
double mu)
Set the orbit from Cartesian parameters.
|
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
SpacecraftState.getPVCoordinates()
Get the
PVCoordinates in orbit definition frame. |
PVCoordinates |
AbstractPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
PVCoordinates |
SpacecraftState.getPVCoordinates(Frame outputFrame)
Get the
PVCoordinates in given output frame. |
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
Ephemeris.getPVCoordinates(AbsoluteDate date,
Frame f)
Get the
PVCoordinates of the body in the selected frame. |
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
TLEPropagator.getPVCoordinates(AbsoluteDate date)
Get the extrapolated position and velocity from an initial TLE.
|
PVCoordinates |
TLESeries.getPVCoordinates(AbsoluteDate date)
Get the extrapolated position and velocity from an initial date.
|
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
IntegratedEphemeris.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
NumericalPropagator.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
Modifier and Type | Field and Description |
---|---|
static PVCoordinates |
PVCoordinates.ZERO
Fixed position/velocity at origin (both p and v are zero vectors).
|
Modifier and Type | Method and Description |
---|---|
PVCoordinates |
PVCoordinatesProvider.getPVCoordinates(AbsoluteDate date,
Frame frame)
Get the
PVCoordinates of the body in the selected frame. |
static PVCoordinates |
PVCoordinates.interpolate(AbsoluteDate date,
boolean useVelocities,
Collection<Pair<AbsoluteDate,PVCoordinates>> sample)
Interpolate position-velocity.
|
PVCoordinates |
PVCoordinates.negate()
Get the opposite of the instance.
|
PVCoordinates |
PVCoordinates.shiftedBy(double dt)
Get a time-shifted state.
|
PVCoordinates |
FieldPVCoordinates.toPVCoordinates()
Convert to a constant position-velocity without derivatives.
|
Modifier and Type | Method and Description |
---|---|
static PVCoordinates |
PVCoordinates.interpolate(AbsoluteDate date,
boolean useVelocities,
Collection<Pair<AbsoluteDate,PVCoordinates>> sample)
Interpolate position-velocity.
|
Constructor and Description |
---|
FieldPVCoordinates(T a,
PVCoordinates pv)
Multiplicative constructor
|
FieldPVCoordinates(T a1,
PVCoordinates pv1,
T a2,
PVCoordinates pv2)
Linear constructor
|
FieldPVCoordinates(T a1,
PVCoordinates pv1,
T a2,
PVCoordinates pv2,
T a3,
PVCoordinates pv3)
Linear constructor
|
FieldPVCoordinates(T a1,
PVCoordinates pv1,
T a2,
PVCoordinates pv2,
T a3,
PVCoordinates pv3,
T a4,
PVCoordinates pv4)
Linear constructor
|
PVCoordinates(double a,
PVCoordinates pv)
Multiplicative constructor
|
PVCoordinates(double a1,
PVCoordinates pv1,
double a2,
PVCoordinates pv2)
Linear constructor
|
PVCoordinates(double a1,
PVCoordinates pv1,
double a2,
PVCoordinates pv2,
double a3,
PVCoordinates pv3)
Linear constructor
|
PVCoordinates(double a1,
PVCoordinates pv1,
double a2,
PVCoordinates pv2,
double a3,
PVCoordinates pv3,
double a4,
PVCoordinates pv4)
Linear constructor
|
PVCoordinates(PVCoordinates start,
PVCoordinates end)
Subtractive constructor
|
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