fr.cnes.sirius.patrius.forces.drag

Interface DragSensitive

All Superinterfaces:

JacobianParametersProvider, Serializable

All Known Implementing Classes:

AeroModel, DragLiftModel, GlobalAeroModel, StelaAeroModel

public interface DragSensitive
extends Serializable, JacobianParametersProvider

Interface for spacecraft that are sensitive to atmospheric drag and lift forces.

Author:

Luc Maisonobe, Pascal Parraud

See Also:

DragForce

Method Summary

Methods

Modifier and Type	Method and Description
void	addDDragAccDParam(SpacecraftState s, Parameter param, double density, Vector3D relativeVelocity, double[] dAccdParam) Compute acceleration derivatives with respect to additional parameters (the ballistic coefficient).
void	addDDragAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel, double density, Vector3D acceleration, Vector3D relativeVelocity, boolean computeGradientPosition, boolean computeGradientVelocity) Compute acceleration derivatives with respect to state parameters (position and velocity).
Vector3D	dragAcceleration(SpacecraftState state, double density, Vector3D relativeVelocity) Compute the acceleration due to drag and the lift.

Methods inherited from interface fr.cnes.sirius.patrius.propagation.numerical.JacobianParametersProvider

getJacobianParameters

Method Detail

dragAcceleration

Vector3D dragAcceleration(SpacecraftState state,
                        double density,
                        Vector3D relativeVelocity)
                          throws PatriusException

Compute the acceleration due to drag and the lift.

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

Parameters:

state - current state information: date, kinematics, attitude

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:

PatriusException - if acceleration cannot be computed

addDDragAccDParam

void addDDragAccDParam(SpacecraftState s,
                     Parameter param,
                     double density,
                     Vector3D relativeVelocity,
                     double[] dAccdParam)
                       throws PatriusException

Compute acceleration derivatives with respect to additional parameters (the ballistic coefficient).

Parameters:

s - spacecraft state

param - parameter

density - the atmospheric density value

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

dAccdParam - acceleration derivatives with respect to ballistic coefficient

Throws:

PatriusException - if derivatives cannot be computed

addDDragAccDState

void addDDragAccDState(SpacecraftState s,
                     double[][] dAccdPos,
                     double[][] dAccdVel,
                     double density,
                     Vector3D acceleration,
                     Vector3D relativeVelocity,
                     boolean computeGradientPosition,
                     boolean computeGradientVelocity)
                       throws PatriusException

Compute acceleration derivatives with respect to state parameters (position and velocity).

Parameters:

s - spacecraft state

dAccdPos - acceleration derivatives with respect to position parameters

dAccdVel - acceleration derivatives with respect to velocity parameters

density - the atmospheric density value

acceleration - the spacecraft acceleration in the inertial frame

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

computeGradientPosition - true if partial derivatives with respect to position should be computed

computeGradientVelocity - true if partial derivatives with respect to position should be computed

Throws:

PatriusException - if derivatives cannot be computed