Package | Description |
---|---|
org.orekit.files.ccsds |
This package provides a parser for orbit data stored in CCSDS Orbit Data Message format.
|
org.orekit.forces.maneuvers |
This package provides models of simple maneuvers.
|
org.orekit.orbits |
This package provides classes to represent orbits.
|
org.orekit.propagation.integration | |
org.orekit.propagation.numerical | |
org.orekit.propagation.semianalytical.dsst |
This package provides an implementation of the Draper Semi-analytical
Satellite Theory (DSST).
|
Modifier and Type | Method and Description |
---|---|
PositionAngle |
OGMFile.getAnomalyType()
Get the type of anomaly (true or mean).
|
Modifier and Type | Method and Description |
---|---|
void |
SmallManeuverAnalyticalModel.getJacobian(Orbit orbit1,
PositionAngle positionAngle,
double[][] jacobian)
Compute the Jacobian of the orbit with respect to maneuver parameters.
|
Modifier and Type | Method and Description |
---|---|
static PositionAngle |
PositionAngle.valueOf(String name)
Returns the enum constant of this type with the specified name.
|
static PositionAngle[] |
PositionAngle.values()
Returns an array containing the constants of this enum type, in
the order they are declared.
|
Modifier and Type | Method and Description |
---|---|
void |
CircularOrbit.addKeplerContribution(PositionAngle type,
double gm,
double[] pDot)
Add the contribution of the Keplerian motion to parameters derivatives
|
void |
CartesianOrbit.addKeplerContribution(PositionAngle type,
double gm,
double[] pDot)
Add the contribution of the Keplerian motion to parameters derivatives
|
void |
EquinoctialOrbit.addKeplerContribution(PositionAngle type,
double gm,
double[] pDot)
Add the contribution of the Keplerian motion to parameters derivatives
|
abstract void |
Orbit.addKeplerContribution(PositionAngle type,
double gm,
double[] pDot)
Add the contribution of the Keplerian motion to parameters derivatives
|
void |
KeplerianOrbit.addKeplerContribution(PositionAngle type,
double gm,
double[] pDot)
Add the contribution of the Keplerian motion to parameters derivatives
|
double |
CircularOrbit.getAlpha(PositionAngle type)
Get the latitude argument.
|
double |
KeplerianOrbit.getAnomaly(PositionAngle type)
Get the anomaly.
|
void |
CartesianOrbit.getJacobianWrtCartesian(PositionAngle type,
double[][] jacobian) |
void |
Orbit.getJacobianWrtCartesian(PositionAngle type,
double[][] jacobian)
Compute the Jacobian of the orbital parameters with respect to the Cartesian parameters.
|
void |
Orbit.getJacobianWrtParameters(PositionAngle type,
double[][] jacobian)
Compute the Jacobian of the Cartesian parameters with respect to the orbital parameters.
|
double |
EquinoctialOrbit.getL(PositionAngle type)
Get the longitude argument.
|
abstract Orbit |
OrbitType.mapArrayToOrbit(double[] array,
PositionAngle type,
AbsoluteDate date,
double mu,
Frame frame)
Convert state array to orbital parameters.
|
abstract void |
OrbitType.mapOrbitToArray(Orbit orbit,
PositionAngle type,
double[] stateVector)
Convert orbit to state array.
|
Constructor and Description |
---|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
CircularOrbit(double a,
double ex,
double ey,
double i,
double raan,
double alpha,
PositionAngle type,
TimeStampedPVCoordinates pvCoordinates,
Frame frame,
double mu)
Creates a new instance.
|
EquinoctialOrbit(double a,
double ex,
double ey,
double hx,
double hy,
double l,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
KeplerianOrbit(double a,
double e,
double i,
double pa,
double raan,
double anomaly,
PositionAngle type,
Frame frame,
AbsoluteDate date,
double mu)
Creates a new instance.
|
Modifier and Type | Method and Description |
---|---|
PositionAngle |
StateMapper.getPositionAngleType()
Get propagation parameter type.
|
protected PositionAngle |
AbstractIntegratedPropagator.getPositionAngleType()
Get propagation parameter type.
|
Modifier and Type | Method and Description |
---|---|
protected abstract StateMapper |
AbstractIntegratedPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
protected void |
AbstractIntegratedPropagator.setPositionAngleType(PositionAngle positionAngleType)
Set position angle type.
|
Constructor and Description |
---|
StateMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Simple constructor.
|
Modifier and Type | Method and Description |
---|---|
PositionAngle |
NumericalPropagator.getPositionAngleType()
Get propagation parameter type.
|
Modifier and Type | Method and Description |
---|---|
protected StateMapper |
NumericalPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
void |
NumericalPropagator.setPositionAngleType(PositionAngle positionAngleType)
Set position angle type.
|
Modifier and Type | Method and Description |
---|---|
protected StateMapper |
DSSTPropagator.createMapper(AbsoluteDate referenceDate,
double mu,
OrbitType orbitType,
PositionAngle positionAngleType,
AttitudeProvider attitudeProvider,
Frame frame)
Create a mapper between raw double components and spacecraft state.
|
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