org.orekit.forces.drag

Class IsotropicDrag

java.lang.Object

org.orekit.forces.drag.IsotropicDrag

All Implemented Interfaces:

DragSensitive

public class IsotropicDrag
extends Object
implements DragSensitive

This class models isotropic drag effects.

The model of this spacecraft is a simple spherical model, this means that all coefficients are constant and do not depend of the direction.

Since:

7.1

Author:

Luc Maisonobe

See Also:

BoxAndSolarArraySpacecraft, IsotropicRadiationCNES95Convention

Field Summary

Fields inherited from interface org.orekit.forces.drag.DragSensitive

DRAG_COEFFICIENT

Constructor Summary

Constructors

Constructor and Description
IsotropicDrag(double crossSection, double dragCoeff) Simple constructor.

Method Summary

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	dragAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, DerivativeStructure density, FieldVector3D<DerivativeStructure> relativeVelocity) Compute the acceleration due to drag, with state derivatives.
Vector3D	dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity) Compute the acceleration due to drag.
FieldVector3D<DerivativeStructure>	dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, String paramName) Compute acceleration due to drag, with parameters derivatives.
ParameterDriver[]	getDragParametersDrivers() Get the drivers for supported parameters.

Methods inherited from class java.lang.Object

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

Methods inherited from interface org.orekit.forces.drag.DragSensitive

getDragCoefficient, getDragParametersNames, setDragCoefficient

Constructor Detail

IsotropicDrag

public IsotropicDrag(double crossSection,
                     double dragCoeff)

Simple constructor.

Parameters:

crossSection - Surface (m²)

dragCoeff - drag coefficient

Method Detail

getDragParametersDrivers

public ParameterDriver[] getDragParametersDrivers()

Get the drivers for supported parameters.

Specified by:

getDragParametersDrivers in interface DragSensitive

Returns:

parameters drivers

dragAcceleration

public Vector3D dragAcceleration(AbsoluteDate date,
                                 Frame frame,
                                 Vector3D position,
                                 Rotation rotation,
                                 double mass,
                                 double density,
                                 Vector3D relativeVelocity)

Compute the acceleration due to drag.

The computation includes all spacecraft specific characteristics like shape, area and coefficients.

Specified by:

dragAcceleration in interface DragSensitive

Parameters:

date - current date

frame - inertial reference frame for state (both orbit and attitude)

position - position of spacecraft in reference frame

rotation - orientation (attitude) of the spacecraft with respect to reference frame

mass - current mass

density - atmospheric density at spacecraft position

relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)

Returns:

spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

dragAcceleration

public FieldVector3D<DerivativeStructure> dragAcceleration(AbsoluteDate date,
                                                           Frame frame,
                                                           FieldVector3D<DerivativeStructure> position,
                                                           FieldRotation<DerivativeStructure> rotation,
                                                           DerivativeStructure mass,
                                                           DerivativeStructure density,
                                                           FieldVector3D<DerivativeStructure> relativeVelocity)

Compute the acceleration due to drag, with state derivatives.

The computation includes all spacecraft specific characteristics like shape, area and coefficients.

Specified by:

dragAcceleration in interface DragSensitive

Parameters:

date - current date

frame - inertial reference frame for state (both orbit and attitude)

position - position of spacecraft in reference frame

rotation - orientation (attitude) of the spacecraft with respect to reference frame

mass - spacecraft mass

density - atmospheric density at spacecraft position

relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)

Returns:

spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

dragAcceleration

public FieldVector3D<DerivativeStructure> dragAcceleration(AbsoluteDate date,
                                                           Frame frame,
                                                           Vector3D position,
                                                           Rotation rotation,
                                                           double mass,
                                                           double density,
                                                           Vector3D relativeVelocity,
                                                           String paramName)
                                                    throws OrekitException

Compute acceleration due to drag, with parameters derivatives.

Specified by:

dragAcceleration in interface DragSensitive

Parameters:

date - current date

frame - inertial reference frame for state (both orbit and attitude)

position - position of spacecraft in reference frame

rotation - orientation (attitude) of the spacecraft with respect to reference frame

mass - current mass

density - atmospheric density at spacecraft position

relativeVelocity - relative velocity of atmosphere with respect to spacecraft, in the same inertial frame as spacecraft orbit (m/s)

paramName - name of the parameter with respect to which derivatives are required

Returns:

spacecraft acceleration in the same inertial frame as spacecraft orbit (m/s²)

Throws:

OrekitException - if derivatives cannot be computed