Package 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	Description
static String	DRAG_COEFFICIENT	Parameter name for drag coefficient.
static String	GLOBAL_DRAG_FACTOR	Parameter name for global multiplicative factor.
static String	LIFT_RATIO	Parameter name for lift ration enabling Jacobian processing.

Method Summary

Modifier and Type	Method	Description
default boolean	dependsOnAttitudeRate()	Check if model depends on attitude's rotation rate or acceleration at a given, fixed date.
<T extends CalculusFieldElement<T>> FieldVector3D<T>	dragAcceleration(FieldSpacecraftState<T> state, T density, FieldVector3D<T> relativeVelocity, T[] parameters)	Compute the acceleration due to drag.
Vector3D	dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity, double[] parameters)	Compute the acceleration due to drag.
List<ParameterDriver>	getDragParametersDrivers()	Get the drivers for supported parameters.

Field Detail

GLOBAL_DRAG_FACTOR

static final String GLOBAL_DRAG_FACTOR

Parameter name for global multiplicative factor.

Since:

12.0

See Also:

Constant Field Values

DRAG_COEFFICIENT

static final String DRAG_COEFFICIENT

Parameter name for drag coefficient.

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

dependsOnAttitudeRate

default boolean dependsOnAttitudeRate()

Check if model depends on attitude's rotation rate or acceleration at a given, fixed date. If false, it essentially means that at most the attitude's rotation is used when computing the acceleration vector. The default implementation returns false as common models for orbital mechanics do not.

Returns:

true if force model depends on attitude derivatives

Since:

12.1

getDragParametersDrivers

List<ParameterDriver> getDragParametersDrivers()

Get the drivers for supported parameters.

Returns:

parameters drivers

Since:

8.0

dragAcceleration

Vector3D dragAcceleration(SpacecraftState state,
                          double density,
                          Vector3D relativeVelocity,
                          double[] parameters)

Compute the acceleration due to drag.

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

Parameters:

state - current state

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)

Since:

12.0

dragAcceleration

<T extends CalculusFieldElement<T>> FieldVector3D<T> dragAcceleration(FieldSpacecraftState<T> state,
                                                                      T density,
                                                                      FieldVector3D<T> relativeVelocity,
                                                                      T[] parameters)

Compute the acceleration due to drag.

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

Type Parameters:

T - instance of a CalculusFieldElement

Parameters:

state - current state

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)

Since:

12.0