org.orekit.tutorials.estimation.performance

Class OrbitDeterminationEngine

java.lang.Object

org.orekit.tutorials.estimation.common.AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

org.orekit.tutorials.estimation.performance.OrbitDeterminationEngine

public class OrbitDeterminationEngine
extends AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Orbit determination engine for performance testing.

Author:

Bryan Cazabonne

Constructor Summary

Constructors

Constructor and Description
OrbitDeterminationEngine(boolean isKalman) Constructor.

Method Summary

Modifier and Type	Method and Description
protected void	compareWithReference(org.orekit.orbits.Orbit estimatedOrbit) Compare the estimated orbit with a reference orbit.
protected void	createGravityField(TutorialOrbitDetermination inputData) Create a gravity field from input parameters.
protected org.orekit.propagation.conversion.NumericalPropagatorBuilder	createPropagatorBuilder(org.orekit.orbits.Orbit referenceOrbit, org.orekit.propagation.conversion.ODEIntegratorBuilder builder, double positionScale) Create a propagator builder from input parameters.
protected double	getMu() Get the central attraction coefficient.
void	runOrbitDetermination(File inputFile) Run the orbit determination.
protected void	setAttitudeProvider(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, org.orekit.attitudes.AttitudeProvider attitudeProvider) Set attitude provider.
protected org.orekit.utils.ParameterDriver[]	setDrag(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, org.orekit.models.earth.atmosphere.Atmosphere atmosphere, org.orekit.forces.drag.DragSensitive spacecraft) Set drag force model.
protected org.orekit.utils.ParameterDriver[]	setGravity(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, org.orekit.bodies.OneAxisEllipsoid body) Set gravity force model.
protected void	setMass(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, double mass) Set satellite mass.
protected org.orekit.utils.ParameterDriver[]	setOceanTides(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, org.orekit.utils.IERSConventions conventions, org.orekit.bodies.OneAxisEllipsoid body, int degree, int order) Set third body attraction force model.
protected org.orekit.utils.ParameterDriver[]	setPolynomialAcceleration(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, String name, org.hipparchus.geometry.euclidean.threed.Vector3D direction, int degree) Set polynomial acceleration force model.
protected org.orekit.utils.ParameterDriver[]	setRelativity(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder) Set relativity force model.
protected org.orekit.utils.ParameterDriver[]	setSolarRadiationPressure(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, org.orekit.bodies.CelestialBody sun, double equatorialRadius, org.orekit.forces.radiation.RadiationSensitive spacecraft) Set solar radiation pressure force model.
protected org.orekit.utils.ParameterDriver[]	setSolidTides(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, org.orekit.utils.IERSConventions conventions, org.orekit.bodies.OneAxisEllipsoid body, org.orekit.bodies.CelestialBody[] solidTidesBodies) Set third body attraction force model.
protected org.orekit.utils.ParameterDriver[]	setThirdBody(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder, org.orekit.bodies.CelestialBody thirdBody) Set third body attraction force model.

Methods inherited from class org.orekit.tutorials.estimation.common.AbstractOrbitDeterminationEngine

run, runKalman, runReference

Methods inherited from class java.lang.Object

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

Constructor Detail

OrbitDeterminationEngine

public OrbitDeterminationEngine(boolean isKalman)

Constructor.

Parameters:

isKalman - true is orbit determination is performed using a Kalman Filter

Method Detail

runOrbitDetermination

public void runOrbitDetermination(File inputFile)
                           throws IOException

Run the orbit determination.

Parameters:

inputFile - in orbit determination file

Throws:

IOException - if file cannot be read properly

createGravityField

protected void createGravityField(TutorialOrbitDetermination inputData)
                           throws NoSuchElementException

Create a gravity field from input parameters.

Specified by:

createGravityField in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

inputData - input data

Throws:

NoSuchElementException - if input parameters are missing

getMu

protected double getMu()

Get the central attraction coefficient.

Specified by:

getMu in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Returns:

central attraction coefficient

createPropagatorBuilder

protected org.orekit.propagation.conversion.NumericalPropagatorBuilder 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.

Specified by:

createPropagatorBuilder in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

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 void setMass(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                       double mass)

Set satellite mass.

Specified by:

setMass in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

propagatorBuilder - propagator builder

mass - initial mass

setGravity

protected org.orekit.utils.ParameterDriver[] setGravity(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                                                        org.orekit.bodies.OneAxisEllipsoid body)

Set gravity force model.

Specified by:

setGravity in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

propagatorBuilder - propagator builder

body - central body

Returns:

drivers for the force model

setOceanTides

protected org.orekit.utils.ParameterDriver[] setOceanTides(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                                                           org.orekit.utils.IERSConventions conventions,
                                                           org.orekit.bodies.OneAxisEllipsoid body,
                                                           int degree,
                                                           int order)

Set third body attraction force model.

Specified by:

setOceanTides in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

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 org.orekit.utils.ParameterDriver[] setSolidTides(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                                                           org.orekit.utils.IERSConventions conventions,
                                                           org.orekit.bodies.OneAxisEllipsoid body,
                                                           org.orekit.bodies.CelestialBody[] solidTidesBodies)

Set third body attraction force model.

Specified by:

setSolidTides in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

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 org.orekit.utils.ParameterDriver[] setThirdBody(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                                                          org.orekit.bodies.CelestialBody thirdBody)

Set third body attraction force model.

Specified by:

setThirdBody in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

propagatorBuilder - propagator builder

thirdBody - third body

Returns:

drivers for the force model

setDrag

protected org.orekit.utils.ParameterDriver[] setDrag(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                                                     org.orekit.models.earth.atmosphere.Atmosphere atmosphere,
                                                     org.orekit.forces.drag.DragSensitive spacecraft)

Set drag force model.

Specified by:

setDrag in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

propagatorBuilder - propagator builder

atmosphere - atmospheric model

spacecraft - spacecraft model

Returns:

drivers for the force model

setSolarRadiationPressure

protected org.orekit.utils.ParameterDriver[] setSolarRadiationPressure(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                                                                       org.orekit.bodies.CelestialBody sun,
                                                                       double equatorialRadius,
                                                                       org.orekit.forces.radiation.RadiationSensitive spacecraft)

Set solar radiation pressure force model.

Specified by:

setSolarRadiationPressure in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

propagatorBuilder - propagator builder

sun - Sun model

equatorialRadius - central body equatorial radius (for shadow computation)

spacecraft - spacecraft model

Returns:

drivers for the force model

setRelativity

protected org.orekit.utils.ParameterDriver[] setRelativity(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder)

Set relativity force model.

Specified by:

setRelativity in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

propagatorBuilder - propagator builder

Returns:

drivers for the force model

setPolynomialAcceleration

protected org.orekit.utils.ParameterDriver[] setPolynomialAcceleration(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                                                                       String name,
                                                                       org.hipparchus.geometry.euclidean.threed.Vector3D direction,
                                                                       int degree)

Set polynomial acceleration force model.

Specified by:

setPolynomialAcceleration in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

propagatorBuilder - propagator builder

name - name of the acceleration

direction - normalized direction of the acceleration

degree - polynomial degree

Returns:

drivers for the force model

setAttitudeProvider

protected void setAttitudeProvider(org.orekit.propagation.conversion.NumericalPropagatorBuilder propagatorBuilder,
                                   org.orekit.attitudes.AttitudeProvider attitudeProvider)

Set attitude provider.

Specified by:

setAttitudeProvider in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

propagatorBuilder - propagator builder

attitudeProvider - attitude provider

compareWithReference

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

Compare the estimated orbit with a reference orbit..

Specified by:

compareWithReference in class AbstractOrbitDeterminationEngine<org.orekit.propagation.conversion.NumericalPropagatorBuilder>

Parameters:

estimatedOrbit - estimated orbit

Throws:

IOException - if input file cannot be read