org.orekit.forces.drag

Interface DragSensitive

All Known Implementing Classes:

BoxAndSolarArraySpacecraft, SphericalSpacecraft

public interface DragSensitive

Interface for spacecraft that are sensitive to atmospheric drag forces.

Author:

Luc Maisonobe, Pascal Parraud

See Also:

DragForce

Field Summary

Fields

Modifier and Type	Field and Description
static String	DRAG_COEFFICIENT Parameter name for drag coefficient enabling jacobian processing.

Method Summary

Methods

Modifier and Type	Method and Description
FieldVector3D<DerivativeStructure>	dragAcceleration(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass, double 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.
double	getDragCoefficient() Get the drag coefficient.
void	setDragCoefficient(double value) Set the drag coefficient.

Field Detail

DRAG_COEFFICIENT

static final String DRAG_COEFFICIENT

Parameter name for drag coefficient enabling jacobian processing.

See Also:

Constant Field Values

Method Detail

dragAcceleration

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

Compute the acceleration due to drag.

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

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)

Throws:

OrekitException - if acceleration cannot be computed

dragAcceleration

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

Compute the acceleration due to drag, with state derivatives.

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

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)

Throws:

OrekitException - if acceleration cannot be computed

dragAcceleration

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.

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

setDragCoefficient

void setDragCoefficient(double value)

Set the drag coefficient.

Parameters:

value - drag coefficient

getDragCoefficient

double getDragCoefficient()

Get the drag coefficient.

Returns:

drag coefficient