IsotropicDrag
, and either
IsotropicRadiationSingleCoefficient
,
IsotropicRadiationClassicalConvention
or IsotropicRadiationCNES95Convention
@Deprecated public class SphericalSpacecraft extends Object implements RadiationSensitive, DragSensitive
The model of this spacecraft is a simple spherical model, this means that all coefficients are constant and do not depend of the direction.
BoxAndSolarArraySpacecraft
,
IsotropicDrag
,
IsotropicRadiationCNES95Convention
ABSORPTION_COEFFICIENT, REFLECTION_COEFFICIENT
DRAG_COEFFICIENT
Constructor and Description |
---|
SphericalSpacecraft(double crossSection,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff)
Deprecated.
Simple constructor.
|
Modifier and Type | Method and Description |
---|---|
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> |
dragAcceleration(AbsoluteDate date,
Frame frame,
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> position,
org.apache.commons.math3.geometry.euclidean.threed.FieldRotation<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> rotation,
org.apache.commons.math3.analysis.differentiation.DerivativeStructure mass,
org.apache.commons.math3.analysis.differentiation.DerivativeStructure density,
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> relativeVelocity)
Deprecated.
Compute the acceleration due to drag, with state derivatives.
|
org.apache.commons.math3.geometry.euclidean.threed.Vector3D |
dragAcceleration(AbsoluteDate date,
Frame frame,
org.apache.commons.math3.geometry.euclidean.threed.Vector3D position,
org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation,
double mass,
double density,
org.apache.commons.math3.geometry.euclidean.threed.Vector3D relativeVelocity)
Deprecated.
Compute the acceleration due to drag.
|
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> |
dragAcceleration(AbsoluteDate date,
Frame frame,
org.apache.commons.math3.geometry.euclidean.threed.Vector3D position,
org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation,
double mass,
double density,
org.apache.commons.math3.geometry.euclidean.threed.Vector3D relativeVelocity,
String paramName)
Deprecated.
Compute acceleration due to drag, with parameters derivatives.
|
double |
getAbsorptionCoefficient()
Deprecated.
Get the absorption coefficient.
|
double |
getDragCoefficient()
Deprecated.
Get the drag coefficient.
|
double |
getReflectionCoefficient()
Deprecated.
Get the specular reflection coefficient.
|
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> position,
org.apache.commons.math3.geometry.euclidean.threed.FieldRotation<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> rotation,
org.apache.commons.math3.analysis.differentiation.DerivativeStructure mass,
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> flux)
Deprecated.
Compute the acceleration due to radiation pressure, with state derivatives.
|
org.apache.commons.math3.geometry.euclidean.threed.Vector3D |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.apache.commons.math3.geometry.euclidean.threed.Vector3D position,
org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation,
double mass,
org.apache.commons.math3.geometry.euclidean.threed.Vector3D flux)
Deprecated.
Compute the acceleration due to radiation pressure.
|
org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.apache.commons.math3.geometry.euclidean.threed.Vector3D position,
org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation,
double mass,
org.apache.commons.math3.geometry.euclidean.threed.Vector3D flux,
String paramName)
Deprecated.
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
void |
setAbsorptionCoefficient(double value)
Deprecated.
Set the absorption coefficient.
|
void |
setDragCoefficient(double value)
Deprecated.
Set the drag coefficient.
|
void |
setReflectionCoefficient(double value)
Deprecated.
Set the specular reflection coefficient.
|
public SphericalSpacecraft(double crossSection, double dragCoeff, double absorptionCoeff, double reflectionCoeff)
crossSection
- Surface (m²)dragCoeff
- drag coefficient (used only for drag)absorptionCoeff
- absorption coefficient between 0.0 an 1.0
(used only for radiation pressure)reflectionCoeff
- specular reflection coefficient between 0.0 an 1.0
(used only for radiation pressure)public org.apache.commons.math3.geometry.euclidean.threed.Vector3D dragAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.Vector3D position, org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.apache.commons.math3.geometry.euclidean.threed.Vector3D relativeVelocity)
The computation includes all spacecraft specific characteristics like shape, area and coefficients.
dragAcceleration
in interface DragSensitive
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)public org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> dragAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> position, org.apache.commons.math3.geometry.euclidean.threed.FieldRotation<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> rotation, org.apache.commons.math3.analysis.differentiation.DerivativeStructure mass, org.apache.commons.math3.analysis.differentiation.DerivativeStructure density, org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> relativeVelocity)
The computation includes all spacecraft specific characteristics like shape, area and coefficients.
dragAcceleration
in interface DragSensitive
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
- spacecraft massdensity
- atmospheric density at spacecraft positionrelativeVelocity
- relative velocity of atmosphere with respect to spacecraft,
in the same inertial frame as spacecraft orbit (m/s)public org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> dragAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.Vector3D position, org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation, double mass, double density, org.apache.commons.math3.geometry.euclidean.threed.Vector3D relativeVelocity, String paramName) throws OrekitException
dragAcceleration
in interface DragSensitive
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)paramName
- name of the parameter with respect to which derivatives are requiredOrekitException
- if derivatives cannot be computedpublic org.apache.commons.math3.geometry.euclidean.threed.Vector3D radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.Vector3D position, org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation, double mass, org.apache.commons.math3.geometry.euclidean.threed.Vector3D flux)
radiationPressureAcceleration
in interface RadiationSensitive
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 massflux
- radiation flux in the same inertial frame as spacecraft orbitpublic org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> position, org.apache.commons.math3.geometry.euclidean.threed.FieldRotation<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> rotation, org.apache.commons.math3.analysis.differentiation.DerivativeStructure mass, org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> flux)
radiationPressureAcceleration
in interface RadiationSensitive
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
- spacecraft massflux
- radiation flux in the same inertial frame as spacecraft orbitpublic org.apache.commons.math3.geometry.euclidean.threed.FieldVector3D<org.apache.commons.math3.analysis.differentiation.DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.apache.commons.math3.geometry.euclidean.threed.Vector3D position, org.apache.commons.math3.geometry.euclidean.threed.Rotation rotation, double mass, org.apache.commons.math3.geometry.euclidean.threed.Vector3D flux, String paramName) throws OrekitException
radiationPressureAcceleration
in interface RadiationSensitive
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 massflux
- radiation flux in the same inertial frame as spacecraft orbitparamName
- name of the parameter with respect to which derivatives are requiredOrekitException
- if acceleration cannot be computedpublic void setDragCoefficient(double value)
setDragCoefficient
in interface DragSensitive
value
- drag coefficientpublic double getDragCoefficient()
getDragCoefficient
in interface DragSensitive
public void setAbsorptionCoefficient(double value)
setAbsorptionCoefficient
in interface RadiationSensitive
value
- absorption coefficientpublic double getAbsorptionCoefficient()
getAbsorptionCoefficient
in interface RadiationSensitive
public void setReflectionCoefficient(double value)
setReflectionCoefficient
in interface RadiationSensitive
value
- specular reflection coefficientpublic double getReflectionCoefficient()
getReflectionCoefficient
in interface RadiationSensitive
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