org.orekit.forces.drag

Interface DragSensitive

All Known Implementing Classes:

BoxAndSolarArraySpacecraft, IsotropicDrag

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.
static String	LIFT_RATIO Parameter name for lift ration enabling Jacobian processing.

Method Summary

Modifier and Type	Method and Description
org.hipparchus.geometry.euclidean.threed.Vector3D	dragAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity, double[] parameters) Compute the acceleration due to drag.
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure>	dragAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity, double[] parameters, String paramName) Compute acceleration due to drag, with parameters derivatives.
<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T>	dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position, org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation, T mass, T density, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> relativeVelocity, T[] parameters) Compute the acceleration due to drag.
ParameterDriver[]	getDragParametersDrivers() Get the drivers for supported parameters.

Field Detail

DRAG_COEFFICIENT

static final String DRAG_COEFFICIENT

Parameter name for drag coefficient enabling Jacobian processing.

See Also:

Constant Field Values

LIFT_RATIO

static final String LIFT_RATIO

Parameter name for lift ration enabling Jacobian processing.

The lift ratio is the proportion of atmosphere modecules that will experience specular reflection when hitting spacecraft instead of experiencing diffuse reflection. The ratio is between 0 and 1, 0 meaning there are no specular reflection, only diffuse reflection, and hence no lift effect.

Since:

9.0

See Also:

Constant Field Values

Method Detail

getDragParametersDrivers

ParameterDriver[] getDragParametersDrivers()

Get the drivers for supported parameters.

Returns:

parameters drivers

Since:

8.0

dragAcceleration

org.hipparchus.geometry.euclidean.threed.Vector3D dragAcceleration(AbsoluteDate date,
                                                                   Frame frame,
                                                                   org.hipparchus.geometry.euclidean.threed.Vector3D position,
                                                                   org.hipparchus.geometry.euclidean.threed.Rotation rotation,
                                                                   double mass,
                                                                   double density,
                                                                   org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity,
                                                                   double[] parameters)
                                                            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)

parameters - values of the force model parameters

Returns:

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

Throws:

OrekitException - if acceleration cannot be computed

dragAcceleration

<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> dragAcceleration(FieldAbsoluteDate<T> date,
                                                                                                                          Frame frame,
                                                                                                                          org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
                                                                                                                          org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
                                                                                                                          T mass,
                                                                                                                          T density,
                                                                                                                          org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> relativeVelocity,
                                                                                                                          T[] parameters)
                                                                                                                   throws OrekitException

Compute the acceleration due to drag.

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

Type Parameters:

T - instance of a RealFieldElement

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)

parameters - values of the force model parameters

Returns:

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

Throws:

OrekitException - if acceleration cannot be computed

Since:

9.0

dragAcceleration

org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> dragAcceleration(AbsoluteDate date,
                                                                                                                                     Frame frame,
                                                                                                                                     org.hipparchus.geometry.euclidean.threed.Vector3D position,
                                                                                                                                     org.hipparchus.geometry.euclidean.threed.Rotation rotation,
                                                                                                                                     double mass,
                                                                                                                                     double density,
                                                                                                                                     org.hipparchus.geometry.euclidean.threed.Vector3D relativeVelocity,
                                                                                                                                     double[] parameters,
                                                                                                                                     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)

parameters - values of the force model parameters

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