public interface RadiationSensitive
SolarRadiationPressure
Modifier and Type | Field and Description |
---|---|
static String |
ABSORPTION_COEFFICIENT
Parameter name for absorption coefficient.
|
static String |
REFLECTION_COEFFICIENT
Parameter name for reflection coefficient.
|
Modifier and Type | Method and Description |
---|---|
ParameterDriver[] |
getRadiationParametersDrivers()
Get the drivers for supported parameters.
|
org.hipparchus.geometry.euclidean.threed.Vector3D |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters)
Compute the acceleration due to radiation pressure.
|
org.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.Vector3D position,
org.hipparchus.geometry.euclidean.threed.Rotation rotation,
double mass,
org.hipparchus.geometry.euclidean.threed.Vector3D flux,
double[] parameters,
String paramName)
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
<T extends org.hipparchus.RealFieldElement<T>> |
radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position,
org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation,
T mass,
org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux,
T[] parameters)
Compute the acceleration due to radiation pressure.
|
static final String ABSORPTION_COEFFICIENT
static final String REFLECTION_COEFFICIENT
ParameterDriver[] getRadiationParametersDrivers()
org.hipparchus.geometry.euclidean.threed.Vector3D radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters) throws OrekitException
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 orbitparameters
- values of the force model parametersOrekitException
- if acceleration cannot be computed<T extends org.hipparchus.RealFieldElement<T>> org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> position, org.hipparchus.geometry.euclidean.threed.FieldRotation<T> rotation, T mass, org.hipparchus.geometry.euclidean.threed.FieldVector3D<T> flux, T[] parameters) throws OrekitException
T
- extends 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 massflux
- radiation flux in the same inertial frame as spacecraft orbitparameters
- values of the force model parametersOrekitException
- if acceleration cannot be computedorg.hipparchus.geometry.euclidean.threed.FieldVector3D<org.hipparchus.analysis.differentiation.DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date, Frame frame, org.hipparchus.geometry.euclidean.threed.Vector3D position, org.hipparchus.geometry.euclidean.threed.Rotation rotation, double mass, org.hipparchus.geometry.euclidean.threed.Vector3D flux, double[] parameters, String paramName) throws OrekitException
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 orbitparameters
- values of the force model parametersparamName
- name of the parameter with respect to which derivatives are requiredOrekitException
- if acceleration cannot be computedCopyright © 2002-2017 CS Systèmes d'information. All rights reserved.