| Package | Description |
|---|---|
| org.orekit.estimation.leastsquares |
The leastsquares package provides an implementation of a batch least
squares estimator engine to perform an orbit determination.
|
| org.orekit.forces.maneuvers |
This package provides models of simple maneuvers.
|
| org.orekit.models.earth.tessellation |
This package provides ways to do tessellation and sampling of zones of
interest over an ellipsoid surface.
|
| org.orekit.orbits |
This package provides classes to represent orbits.
|
| org.orekit.propagation |
Propagation
|
| org.orekit.propagation.analytical |
Top level package for analytical propagators.
|
| org.orekit.propagation.analytical.gnss |
This package provides classes to propagate GNSS orbits.
|
| org.orekit.propagation.analytical.tle |
This package provides classes to read and extrapolate tle's.
|
| org.orekit.propagation.conversion |
This package provides tools to convert a given propagator or a set of
SpacecraftState into another propagator. |
| org.orekit.propagation.events |
This package provides interfaces and classes dealing with events occurring during propagation.
|
| org.orekit.propagation.integration |
Utilities for integration-based propagators (both numerical and semi-analytical).
|
| org.orekit.propagation.numerical |
Top level package for numerical propagators.
|
| org.orekit.propagation.semianalytical.dsst |
This package provides an implementation of the Draper Semi-analytical
Satellite Theory (DSST).
|
| org.orekit.propagation.semianalytical.dsst.forces |
This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
|
| org.orekit.propagation.semianalytical.dsst.utilities |
This package provides utilities for Draper Semi-analytical Satellite Theory (DSST).
|
| Modifier and Type | Method | Description |
|---|---|---|
void |
BatchLSObserver.evaluationPerformed(int iterationsCount,
int evaluationsCount,
Orbit[] orbits,
ParameterDriversList estimatedOrbitalParameters,
ParameterDriversList estimatedPropagatorParameters,
ParameterDriversList estimatedMeasurementsParameters,
EstimationsProvider evaluationsProvider,
org.hipparchus.optim.nonlinear.vector.leastsquares.LeastSquaresProblem.Evaluation lspEvaluation) |
Notification callback for the end of each evaluation.
|
| Modifier and Type | Method | Description |
|---|---|---|
Orbit |
SmallManeuverAnalyticalModel.apply(Orbit orbit1) |
Compute the effect of the maneuver on an orbit.
|
| Modifier and Type | Method | Description |
|---|---|---|
Orbit |
SmallManeuverAnalyticalModel.apply(Orbit orbit1) |
Compute the effect of the maneuver on an orbit.
|
void |
SmallManeuverAnalyticalModel.getJacobian(Orbit orbit1,
PositionAngle positionAngle,
double[][] jacobian) |
Compute the Jacobian of the orbit with respect to maneuver parameters.
|
| Constructor | Description |
|---|---|
AlongTrackAiming(OneAxisEllipsoid ellipsoid,
Orbit orbit,
boolean isAscending) |
Simple constructor.
|
| Modifier and Type | Class | Description |
|---|---|---|
class |
CartesianOrbit |
This class holds Cartesian orbital parameters.
|
class |
CircularOrbit |
This class handles circular orbital parameters.
|
class |
EquinoctialOrbit |
This class handles equinoctial orbital parameters, which can support both
circular and equatorial orbits.
|
class |
KeplerianOrbit |
This class handles traditional Keplerian orbital parameters.
|
| Modifier and Type | Method | Description |
|---|---|---|
abstract Orbit |
OrbitType.convertType(Orbit orbit) |
Convert an orbit to the instance type.
|
abstract Orbit |
OrbitType.mapArrayToOrbit(double[] array,
double[] arrayDot,
PositionAngle type,
AbsoluteDate date,
double mu,
Frame frame) |
Convert state array to orbital parameters.
|
abstract Orbit |
Orbit.shiftedBy(double dt) |
Get a time-shifted orbit.
|
abstract Orbit |
FieldOrbit.toOrbit() |
Transforms the FieldOrbit instance into an Orbit instance.
|
| Modifier and Type | Method | Description |
|---|---|---|
abstract Orbit |
OrbitType.convertType(Orbit orbit) |
Convert an orbit to the instance type.
|
abstract ParameterDriversList |
OrbitType.getDrivers(double dP,
Orbit orbit,
PositionAngle type) |
Get parameters drivers initialized from a reference orbit.
|
abstract void |
OrbitType.mapOrbitToArray(Orbit orbit,
PositionAngle type,
double[] stateVector,
double[] stateVectorDot) |
Convert orbit to state array.
|
protected double[] |
OrbitType.scale(double dP,
Orbit orbit) |
Compute scaling factor for parameters drivers.
|
| Modifier and Type | Method | Description |
|---|---|---|
CartesianOrbit |
CartesianOrbit.interpolate(AbsoluteDate date,
Stream<Orbit> sample) |
Get an interpolated instance.
|
CircularOrbit |
CircularOrbit.interpolate(AbsoluteDate date,
Stream<Orbit> sample) |
Get an interpolated instance.
|
EquinoctialOrbit |
EquinoctialOrbit.interpolate(AbsoluteDate date,
Stream<Orbit> sample) |
Get an interpolated instance.
|
KeplerianOrbit |
KeplerianOrbit.interpolate(AbsoluteDate date,
Stream<Orbit> sample) |
Get an interpolated instance.
|
| Constructor | Description |
|---|---|
CartesianOrbit(Orbit op) |
Constructor from any kind of orbital parameters.
|
CircularOrbit(Orbit op) |
Constructor from any kind of orbital parameters.
|
EquinoctialOrbit(Orbit op) |
Constructor from any kind of orbital parameters.
|
KeplerianOrbit(Orbit op) |
Constructor from any kind of orbital parameters.
|
| Modifier and Type | Method | Description |
|---|---|---|
Orbit |
SpacecraftState.getOrbit() |
Gets the current orbit.
|
| Constructor | Description |
|---|---|
SpacecraftState(Orbit orbit) |
Build a spacecraft state from orbit only.
|
SpacecraftState(Orbit orbit,
double mass) |
Create a new instance from orbit and mass.
|
SpacecraftState(Orbit orbit,
double mass,
Map<String,double[]> additional) |
Create a new instance from orbit and mass.
|
SpacecraftState(Orbit orbit,
Map<String,double[]> additional) |
Build a spacecraft state from orbit only.
|
SpacecraftState(Orbit orbit,
Attitude attitude) |
Build a spacecraft state from orbit and attitude provider.
|
SpacecraftState(Orbit orbit,
Attitude attitude,
double mass) |
Build a spacecraft state from orbit, attitude provider and mass.
|
SpacecraftState(Orbit orbit,
Attitude attitude,
double mass,
Map<String,double[]> additional) |
Build a spacecraft state from orbit, attitude provider and mass.
|
SpacecraftState(Orbit orbit,
Attitude attitude,
Map<String,double[]> additional) |
Build a spacecraft state from orbit and attitude provider.
|
| Modifier and Type | Method | Description |
|---|---|---|
Orbit |
J2DifferentialEffect.apply(Orbit orbit1) |
Compute the effect of the maneuver on an orbit.
|
protected abstract Orbit |
AbstractAnalyticalPropagator.propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
protected Orbit |
AdapterPropagator.propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
protected Orbit |
AggregateBoundedPropagator.propagateOrbit(AbsoluteDate date) |
|
protected Orbit |
Ephemeris.propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
protected Orbit |
KeplerianPropagator.propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
| Modifier and Type | Method | Description |
|---|---|---|
Orbit |
J2DifferentialEffect.apply(Orbit orbit1) |
Compute the effect of the maneuver on an orbit.
|
| Constructor | Description |
|---|---|
EcksteinHechlerPropagator(Orbit initialOrbit,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from orbit and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
double mass,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from orbit, mass and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
double mass,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from orbit, mass and potential provider.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from orbit, attitude provider and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mass,
double referenceRadius,
double mu,
double c20,
double c30,
double c40,
double c50,
double c60) |
Build a propagator from orbit, attitude provider, mass and potential.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mass,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from orbit, attitude provider, mass and potential provider.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitude,
double mass,
UnnormalizedSphericalHarmonicsProvider provider,
UnnormalizedSphericalHarmonicsProvider.UnnormalizedSphericalHarmonics harmonics) |
Private helper constructor.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from orbit, attitude provider and potential provider.
|
EcksteinHechlerPropagator(Orbit initialOrbit,
UnnormalizedSphericalHarmonicsProvider provider) |
Build a propagator from orbit and potential provider.
|
J2DifferentialEffect(Orbit orbit0,
Orbit orbit1,
boolean applyBefore,
double referenceRadius,
double mu,
double j2) |
Simple constructor.
|
J2DifferentialEffect(Orbit orbit0,
Orbit orbit1,
boolean applyBefore,
UnnormalizedSphericalHarmonicsProvider gravityField) |
Simple constructor.
|
KeplerianPropagator(Orbit initialOrbit) |
Build a propagator from orbit only.
|
KeplerianPropagator(Orbit initialOrbit,
double mu) |
Build a propagator from orbit and central attraction coefficient μ.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv) |
Build a propagator from orbit and attitude provider.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mu) |
Build a propagator from orbit, attitude provider and central attraction
coefficient μ.
|
KeplerianPropagator(Orbit initialOrbit,
AttitudeProvider attitudeProv,
double mu,
double mass) |
Build propagator from orbit, attitude provider, central attraction
coefficient μ and mass.
|
| Modifier and Type | Method | Description |
|---|---|---|
protected Orbit |
GPSPropagator.propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
| Modifier and Type | Method | Description |
|---|---|---|
protected Orbit |
TLEPropagator.propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
| Modifier and Type | Method | Description |
|---|---|---|
protected Orbit |
AbstractPropagatorBuilder.createInitialOrbit() |
Build an initial orbit using the current selected parameters.
|
| Modifier and Type | Method | Description |
|---|---|---|
org.hipparchus.ode.AbstractIntegrator |
AdamsBashforthIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
AdamsMoultonIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
ClassicalRungeKuttaIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
DormandPrince54IntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
DormandPrince853IntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
EulerIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
GillIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
GraggBulirschStoerIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
HighamHall54IntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
LutherIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
MidpointIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
ODEIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
org.hipparchus.ode.AbstractIntegrator |
ThreeEighthesIntegratorBuilder.buildIntegrator(Orbit orbit,
OrbitType orbitType) |
Build a first order integrator.
|
void |
AbstractPropagatorBuilder.resetOrbit(Orbit newOrbit) |
Reset the orbit in the propagator builder.
|
| Constructor | Description |
|---|---|
AbstractPropagatorBuilder(Orbit templateOrbit,
PositionAngle positionAngle,
double positionScale,
boolean addDriverForCentralAttraction) |
Build a new instance.
|
EcksteinHechlerPropagatorBuilder(Orbit templateOrbit,
double referenceRadius,
double mu,
TideSystem tideSystem,
double c20,
double c30,
double c40,
double c50,
double c60,
OrbitType orbitType,
PositionAngle positionAngle,
double positionScale) |
Build a new instance.
|
EcksteinHechlerPropagatorBuilder(Orbit templateOrbit,
UnnormalizedSphericalHarmonicsProvider provider,
PositionAngle positionAngle,
double positionScale) |
Build a new instance.
|
KeplerianPropagatorBuilder(Orbit templateOrbit,
PositionAngle positionAngle,
double positionScale) |
Build a new instance.
|
NumericalPropagatorBuilder(Orbit referenceOrbit,
ODEIntegratorBuilder builder,
PositionAngle positionAngle,
double positionScale) |
Build a new instance.
|
| Constructor | Description |
|---|---|
AlignmentDetector(double threshold,
Orbit orbit,
PVCoordinatesProvider body,
double alignAngle) |
Build a new alignment detector.
|
AlignmentDetector(Orbit orbit,
PVCoordinatesProvider body,
double alignAngle) |
Build a new alignment detector.
|
ApsideDetector(double threshold,
Orbit orbit) |
Build a new instance.
|
ApsideDetector(Orbit orbit) |
Build a new instance.
|
NodeDetector(double threshold,
Orbit orbit,
Frame frame) |
Build a new instance.
|
NodeDetector(Orbit orbit,
Frame frame) |
Build a new instance.
|
| Modifier and Type | Method | Description |
|---|---|---|
protected Orbit |
IntegratedEphemeris.propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
| Modifier and Type | Method | Description |
|---|---|---|
static double[][] |
NumericalPropagator.tolerances(double dP,
Orbit orbit,
OrbitType type) |
Estimate tolerance vectors for integrators.
|
| Modifier and Type | Method | Description |
|---|---|---|
static double[][] |
DSSTPropagator.tolerances(double dP,
Orbit orbit) |
Estimate tolerance vectors for an AdaptativeStepsizeIntegrator.
|
| Modifier and Type | Method | Description |
|---|---|---|
double[] |
ShortPeriodTerms.value(Orbit meanOrbit) |
Evaluate the contributions of the short period terms.
|
| Constructor | Description |
|---|---|
AuxiliaryElements(Orbit orbit,
int retrogradeFactor) |
Simple constructor.
|
Copyright © 2002-2019 CS Systèmes d'information. All rights reserved.