BoxAndSolarArraySpacecraft
, IsotropicDrag
public interface DragSensitive
DragForce
Modifier and Type | Field | 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.
|
Modifier and Type | Method | 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>> |
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.
|
static final String DRAG_COEFFICIENT
static final String LIFT_RATIO
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.
ParameterDriver[] getDragParametersDrivers()
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)
The computation includes all spacecraft specific characteristics like shape, area and coefficients.
date
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- current massdensity
- atmospheric density at spacecraft positionrelativeVelocity
- 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<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)
The computation includes all spacecraft specific characteristics like shape, area and coefficients.
T
- instance of a RealFieldElementdate
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- current massdensity
- atmospheric density at spacecraft positionrelativeVelocity
- relative velocity of atmosphere with respect to spacecraft,
in the same inertial frame as spacecraft orbit (m/s)parameters
- values of the force model parametersorg.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)
date
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- current massdensity
- atmospheric density at spacecraft positionrelativeVelocity
- relative velocity of atmosphere with respect to spacecraft,
in the same inertial frame as spacecraft orbit (m/s)parameters
- values of the force model parametersparamName
- name of the parameter with respect to which derivatives are requiredCopyright © 2002-2019 CS Systèmes d'information. All rights reserved.