org.orekit.tutorials.estimation.common

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

java.lang.Object

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

Type Parameters:

T - type of the propagator builder

Direct Known Subclasses:

DSSTOrbitDetermination, NumericalOrbitDetermination

public abstract class AbstractOrbitDetermination<T extends org.orekit.propagation.conversion.IntegratedPropagatorBuilder>
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	createGravityField(KeyValueFileParser<ParameterKey> parser) 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 abstract double	getMu() Get the central attraction coefficient.
protected void	run(File input) Run the program.
protected abstract void	setAttitudeProvider(T propagatorBuilder, org.orekit.attitudes.AttitudeProvider attitudeProvider) Set attitude provider.
protected abstract 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 org.orekit.utils.ParameterDriver[]	setGravity(T propagatorBuilder, org.orekit.bodies.OneAxisEllipsoid body) Set gravity force model.
protected abstract void	setMass(T propagatorBuilder, double mass) Set satellite mass.
protected abstract 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 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 org.orekit.utils.ParameterDriver[]	setRelativity(T propagatorBuilder) Set relativity force model.
protected abstract org.orekit.utils.ParameterDriver[]	setSolarRadiationPressure(T propagatorBuilder, org.orekit.bodies.CelestialBody sun, double equatorialRadius, org.orekit.forces.radiation.RadiationSensitive spacecraft) Set solar radiation pressure force model.
protected abstract 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 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(KeyValueFileParser<ParameterKey> parser)
                                    throws NoSuchElementException

Create a gravity field from input parameters.

Parameters:

parser - input file parser

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

Set solar radiation pressure force model.

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 abstract org.orekit.utils.ParameterDriver[] setRelativity(T propagatorBuilder)

Set relativity force model.

Parameters:

propagatorBuilder - propagator builder

Returns:

drivers for the force model

setPolynomialAcceleration

protected abstract 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

setAttitudeProvider

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

Set attitude provider.

Parameters:

propagatorBuilder - propagator builder

attitudeProvider - attitude provider

run

protected void run(File input)
            throws IOException

Run the program.

Parameters:

input - input file

Throws:

IOException - if input files cannot be read