org.orekit.tutorials.estimation.common

Class AbstractOrbitDetermination<T extends org.orekit.propagation.conversion.PropagatorBuilder>

java.lang.Object

org.orekit.tutorials.estimation.common.AbstractOrbitDetermination<T>

Type Parameters:

T - type of the propagator builder

Direct Known Subclasses:

DSSTOrbitDetermination, GNSSOrbitDetermination, KalmanNumericalOrbitDetermination, LaserRangingOrbitDetermination, NumericalOrbitDetermination, TLEBasedOrbitDetermination

public abstract class AbstractOrbitDetermination<T extends org.orekit.propagation.conversion.PropagatorBuilder>
extends Object

Base class for Orekit orbit determination tutorials.

Author:

Luc Maisonobe, Bryan Cazabonne

Constructor Summary

Constructors

Constructor and Description
AbstractOrbitDetermination()

Method Summary

Modifier and Type	Method and Description
protected abstract void	compareWithReference(org.orekit.orbits.Orbit estimatedOrbit) Compare the estimated orbit with a reference orbit.
protected abstract void	createGravityField(TutorialOrbitDetermination inputData) Create a gravity field from input parameters.
protected abstract T	createPropagatorBuilder(org.orekit.orbits.Orbit referenceOrbit, org.orekit.propagation.conversion.ODEIntegratorBuilder builder, double positionScale) Create a propagator builder from input parameters.
protected void	finish(org.orekit.propagation.Propagator[] estimated) Initialization just after orekit-data setting.
protected abstract double	getMu() Get the central attraction coefficient.
protected void	init(TutorialOrbitDetermination inputData) Initialization just after orekit-data setting.
protected void	run(File input) Run the program.
protected void	runKalman(File input) Run the program.
protected org.orekit.orbits.Orbit	runReference(File input, org.hipparchus.geometry.euclidean.threed.Vector3D refPosition, org.hipparchus.geometry.euclidean.threed.Vector3D refVelocity, org.orekit.utils.ParameterDriversList refPropagationParameters, org.orekit.time.AbsoluteDate finalDate) Use the physical models in the input file.
protected abstract void	setAttitudeProvider(T propagatorBuilder, org.orekit.attitudes.AttitudeProvider attitudeProvider) Set attitude provider.
protected abstract List<org.orekit.utils.ParameterDriver>	setDrag(T propagatorBuilder, org.orekit.models.earth.atmosphere.Atmosphere atmosphere, org.orekit.forces.drag.DragSensitive spacecraft) Set drag force model.
protected abstract List<org.orekit.utils.ParameterDriver>	setGravity(T propagatorBuilder, org.orekit.bodies.OneAxisEllipsoid body) Set gravity force model.
protected abstract List<org.orekit.utils.ParameterDriver>	setManeuver(T propagatorBuilder, org.orekit.time.AbsoluteDate fireDate, double duration, double thrust, double isp, org.hipparchus.geometry.euclidean.threed.Vector3D direction, String name) Set maneuver model.
protected abstract void	setMass(T propagatorBuilder, double mass) Set satellite mass.
protected abstract List<org.orekit.utils.ParameterDriver>	setOceanTides(T propagatorBuilder, org.orekit.utils.IERSConventions conventions, org.orekit.bodies.OneAxisEllipsoid body, int degree, int order) Set third body attraction force model.
protected abstract List<org.orekit.utils.ParameterDriver>	setPolynomialAcceleration(T propagatorBuilder, String name, org.hipparchus.geometry.euclidean.threed.Vector3D direction, int degree) Set polynomial acceleration force model.
protected abstract List<org.orekit.utils.ParameterDriver>	setRelativity(T propagatorBuilder) Set relativity force model.
protected abstract List<org.orekit.utils.ParameterDriver>	setSolarRadiationPressure(T propagatorBuilder, org.orekit.bodies.CelestialBody sun, org.orekit.bodies.OneAxisEllipsoid earth, org.orekit.forces.radiation.RadiationSensitive spacecraft) Set solar radiation pressure force model.
protected abstract List<org.orekit.utils.ParameterDriver>	setSolidTides(T propagatorBuilder, org.orekit.utils.IERSConventions conventions, org.orekit.bodies.OneAxisEllipsoid body, org.orekit.bodies.CelestialBody[] solidTidesBodies) Set third body attraction force model.
protected abstract List<org.orekit.utils.ParameterDriver>	setThirdBody(T propagatorBuilder, org.orekit.bodies.CelestialBody thirdBody) Set third body attraction force model.

Methods inherited from class java.lang.Object

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait

Constructor Detail

AbstractOrbitDetermination

public AbstractOrbitDetermination()

Method Detail

createGravityField

protected abstract void createGravityField(TutorialOrbitDetermination inputData)
                                    throws NoSuchElementException

Create a gravity field from input parameters.

Parameters:

inputData - input data

Throws:

NoSuchElementException - if input parameters are missing

getMu

protected abstract double getMu()

Get the central attraction coefficient.

Returns:

central attraction coefficient

createPropagatorBuilder

protected abstract T createPropagatorBuilder(org.orekit.orbits.Orbit referenceOrbit,
                                             org.orekit.propagation.conversion.ODEIntegratorBuilder builder,
                                             double positionScale)

Create a propagator builder from input parameters.

The advantage of using the DSST instead of the numerical propagator is that it is possible to use greater values for the minimum and maximum integration steps.

Parameters:

referenceOrbit - reference orbit from which real orbits will be built

builder - first order integrator builder

positionScale - scaling factor used for orbital parameters normalization (typically set to the expected standard deviation of the position)

Returns:

propagator builder

setMass

protected abstract void setMass(T propagatorBuilder,
                                double mass)

Set satellite mass.

Parameters:

propagatorBuilder - propagator builder

mass - initial mass

setGravity

protected abstract List<org.orekit.utils.ParameterDriver> setGravity(T propagatorBuilder,
                                                                     org.orekit.bodies.OneAxisEllipsoid body)

Set gravity force model.

Parameters:

propagatorBuilder - propagator builder

body - central body

Returns:

drivers for the force model

setOceanTides

protected abstract List<org.orekit.utils.ParameterDriver> setOceanTides(T propagatorBuilder,
                                                                        org.orekit.utils.IERSConventions conventions,
                                                                        org.orekit.bodies.OneAxisEllipsoid body,
                                                                        int degree,
                                                                        int order)

Set third body attraction force model.

Parameters:

propagatorBuilder - propagator builder

conventions - IERS conventions to use

body - central body

degree - degree of the tide model to load

order - order of the tide model to load

Returns:

drivers for the force model

setSolidTides

protected abstract List<org.orekit.utils.ParameterDriver> setSolidTides(T propagatorBuilder,
                                                                        org.orekit.utils.IERSConventions conventions,
                                                                        org.orekit.bodies.OneAxisEllipsoid body,
                                                                        org.orekit.bodies.CelestialBody[] solidTidesBodies)

Set third body attraction force model.

Parameters:

propagatorBuilder - propagator builder

conventions - IERS conventions to use

body - central body

solidTidesBodies - third bodies generating solid tides

Returns:

drivers for the force model

setThirdBody

protected abstract List<org.orekit.utils.ParameterDriver> setThirdBody(T propagatorBuilder,
                                                                       org.orekit.bodies.CelestialBody thirdBody)

Set third body attraction force model.

Parameters:

propagatorBuilder - propagator builder

thirdBody - third body

Returns:

drivers for the force model

setDrag

protected abstract List<org.orekit.utils.ParameterDriver> setDrag(T propagatorBuilder,
                                                                  org.orekit.models.earth.atmosphere.Atmosphere atmosphere,
                                                                  org.orekit.forces.drag.DragSensitive spacecraft)

Set drag force model.

Parameters:

propagatorBuilder - propagator builder

atmosphere - atmospheric model

spacecraft - spacecraft model

Returns:

drivers for the force model

setSolarRadiationPressure

protected abstract List<org.orekit.utils.ParameterDriver> setSolarRadiationPressure(T propagatorBuilder,
                                                                                    org.orekit.bodies.CelestialBody sun,
                                                                                    org.orekit.bodies.OneAxisEllipsoid earth,
                                                                                    org.orekit.forces.radiation.RadiationSensitive spacecraft)

Set solar radiation pressure force model.

Parameters:

propagatorBuilder - propagator builder

sun - Sun model

earth - Earth body shape

spacecraft - spacecraft model

Returns:

drivers for the force model

setRelativity

protected abstract List<org.orekit.utils.ParameterDriver> setRelativity(T propagatorBuilder)

Set relativity force model.

Parameters:

propagatorBuilder - propagator builder

Returns:

drivers for the force model

setPolynomialAcceleration

protected abstract List<org.orekit.utils.ParameterDriver> setPolynomialAcceleration(T propagatorBuilder,
                                                                                    String name,
                                                                                    org.hipparchus.geometry.euclidean.threed.Vector3D direction,
                                                                                    int degree)

Set polynomial acceleration force model.

Parameters:

propagatorBuilder - propagator builder

name - name of the acceleration

direction - normalized direction of the acceleration

degree - polynomial degree

Returns:

drivers for the force model

setManeuver

protected abstract List<org.orekit.utils.ParameterDriver> setManeuver(T propagatorBuilder,
                                                                      org.orekit.time.AbsoluteDate fireDate,
                                                                      double duration,
                                                                      double thrust,
                                                                      double isp,
                                                                      org.hipparchus.geometry.euclidean.threed.Vector3D direction,
                                                                      String name)

Set maneuver model.

Parameters:

propagatorBuilder - propagator builder

fireDate - maneuver date

duration - the duration of the thrust (s) (if negative, the date is considered to be the stop date)

thrust - the thrust force (N)

isp - engine specific impulse (s)

direction - the acceleration direction in satellite frame.

name - of the maneuver

Returns:

drivers for the force mode

setAttitudeProvider

protected abstract void setAttitudeProvider(T propagatorBuilder,
                                            org.orekit.attitudes.AttitudeProvider attitudeProvider)

Set attitude provider.

Parameters:

propagatorBuilder - propagator builder

attitudeProvider - attitude provider

compareWithReference

protected abstract void compareWithReference(org.orekit.orbits.Orbit estimatedOrbit)
                                      throws IOException

Compare the estimated orbit with a reference orbit.

Parameters:

estimatedOrbit - estimated orbit

Throws:

IOException - Input file cannot be opened

init

protected void init(TutorialOrbitDetermination inputData)

Initialization just after orekit-data setting.

By default, does nothing.

Parameters:

inputData - input data

finish

protected void finish(org.orekit.propagation.Propagator[] estimated)

Initialization just after orekit-data setting.

By default, does nothing.

Parameters:

estimated - estimated propagators

run

protected void run(File input)
            throws IOException

Run the program.

This method uses a batch least squares algorithms to perform the orbit determination.

Parameters:

input - input file

Throws:

IOException - if input files cannot be read

runKalman

protected void runKalman(File input)
                  throws IOException

Run the program.

This method uses an Extended Kalman Filter to perform the orbit determination.

Parameters:

input - input file

Throws:

IOException - if input files cannot be read

runReference

protected org.orekit.orbits.Orbit runReference(File input,
                                               org.hipparchus.geometry.euclidean.threed.Vector3D refPosition,
                                               org.hipparchus.geometry.euclidean.threed.Vector3D refVelocity,
                                               org.orekit.utils.ParameterDriversList refPropagationParameters,
                                               org.orekit.time.AbsoluteDate finalDate)
                                        throws IOException

Use the physical models in the input file. Incorporate the initial reference values And run the propagation until the last measurement to get the reference orbit at the same date as the Kalman filter

Parameters:

input - Input configuration file

refPosition - Initial reference position

refVelocity - Initial reference velocity

refPropagationParameters - Reference propagation parameters

finalDate - The final date to usefinal dateame date as the Kalman filter

Returns:

reference orbit at the same data as the Kalman Filter

Throws:

IOException - Input file cannot be opened