DragSensitive, RadiationSensitivepublic class BoxAndSolarArraySpacecraft extends Object implements RadiationSensitive, DragSensitive
The body can be either a simple parallelepipedic box aligned with spacecraft axes or a set of facets defined by their area and normal vector. This should handle accurately most spacecraft shapes.
The solar array rotation with respect to satellite body can be either the best lighting orientation (i.e. Sun exactly in solar array meridian plane defined by solar array rotation axis and solar array normal vector) or a rotation evolving linearly according to a start position and an angular rate (which can be set to 0 for non-rotating panels, which may occur in special modes or during contingencies).
The lift component of the drag force can be optionally considered. It should probably only be used for reentry computation, with much denser atmosphere than in regular orbit propagation. The lift component is computed using a ratio of molecules that experience specular reflection instead of diffuse reflection (absorption followed by outgassing at negligible velocity). Without lift (i.e. when the lift ratio is set to 0), drag force is along atmosphere relative velocity. With lift (i.e. when the lift ratio is set to any value between 0 and 1), the drag force depends on both relative velocity direction and facets normal orientation. For a single panel, if the relative velocity is head-on (i.e. aligned with the panel normal), the force will be in the same direction with and without lift, but the magnitude with lift ratio set to 1.0 will be twice the magnitude with lift ratio set to 0.0 (because atmosphere molecules bounces backward at same velocity in case of specular reflection).
This model does not take cast shadow between body and solar array into account.
| Modifier and Type | Class | Description |
|---|---|---|
static class |
BoxAndSolarArraySpacecraft.Facet |
Class representing a single facet of a convex spacecraft body.
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DRAG_COEFFICIENT, LIFT_RATIOABSORPTION_COEFFICIENT, REFLECTION_COEFFICIENT| Constructor | Description |
|---|---|
BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff) |
Build a spacecraft model with best lighting of solar array.
|
BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
double dragCoeff,
double liftRatio,
double absorptionCoeff,
double reflectionCoeff) |
Build a spacecraft model with best lighting of solar array.
|
BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff) |
Build a spacecraft model with linear rotation of solar array.
|
BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double liftRatio,
double absorptionCoeff,
double reflectionCoeff) |
Build a spacecraft model with linear rotation of solar array.
|
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff) |
Build a spacecraft model with best lighting of solar array.
|
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
double dragCoeff,
double liftRatio,
double absorptionCoeff,
double reflectionCoeff) |
Build a spacecraft model with best lighting of solar array.
|
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff) |
Build a spacecraft model with linear rotation of solar array.
|
BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double liftRatio,
double absorptionCoeff,
double reflectionCoeff) |
Build a spacecraft model with linear rotation of solar array.
|
| Modifier and Type | Method | Description |
|---|---|---|
Vector3D |
dragAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
double density,
Vector3D relativeVelocity,
double[] parameters) |
Compute the acceleration due to drag.
|
FieldVector3D<DerivativeStructure> |
dragAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
double density,
Vector3D relativeVelocity,
double[] parameters,
String paramName) |
Compute acceleration due to drag, with parameters derivatives.
|
<T extends RealFieldElement<T>> |
dragAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
T density,
FieldVector3D<T> relativeVelocity,
T[] parameters) |
Compute the acceleration due to drag.
|
ParameterDriver[] |
getDragParametersDrivers() |
Get the drivers for supported parameters.
|
FieldVector3D<DerivativeStructure> |
getNormal(AbsoluteDate date,
Frame frame,
FieldVector3D<DerivativeStructure> position,
FieldRotation<DerivativeStructure> rotation) |
Get solar array normal in spacecraft frame.
|
Vector3D |
getNormal(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation) |
Get solar array normal in spacecraft frame.
|
<T extends RealFieldElement<T>> |
getNormal(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation) |
Get solar array normal in spacecraft frame.
|
ParameterDriver[] |
getRadiationParametersDrivers() |
Get the drivers for supported parameters.
|
Vector3D |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters) |
Compute the acceleration due to radiation pressure.
|
FieldVector3D<DerivativeStructure> |
radiationPressureAcceleration(AbsoluteDate date,
Frame frame,
Vector3D position,
Rotation rotation,
double mass,
Vector3D flux,
double[] parameters,
String paramName) |
Compute the acceleration due to radiation pressure, with parameters derivatives.
|
<T extends RealFieldElement<T>> |
radiationPressureAcceleration(FieldAbsoluteDate<T> date,
Frame frame,
FieldVector3D<T> position,
FieldRotation<T> rotation,
T mass,
FieldVector3D<T> flux,
T[] parameters) |
Compute the acceleration due to radiation pressure.
|
public BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff)
This constructor builds an instance that completely ignores lift
in atmospheric drag (the value of lift coefficient is set to zero,
and there are no drivers to change it).
Solar arrays orientation will be such that at each time the Sun direction will always be in the solar array meridian plane defined by solar array rotation axis and solar array normal vector.
xLength - length of the body along its X axis (m)yLength - length of the body along its Y axis (m)zLength - length of the body along its Z axis (m)sun - sun modelsolarArrayArea - area of the solar array (m²)solarArrayAxis - solar array rotation axis in satellite framedragCoeff - 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 BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
double dragCoeff,
double liftRatio,
double absorptionCoeff,
double reflectionCoeff)
Solar arrays orientation will be such that at each time the Sun direction will always be in the solar array meridian plane defined by solar array rotation axis and solar array normal vector.
xLength - length of the body along its X axis (m)yLength - length of the body along its Y axis (m)zLength - length of the body along its Z axis (m)sun - sun modelsolarArrayArea - area of the solar array (m²)solarArrayAxis - solar array rotation axis in satellite framedragCoeff - drag coefficient (used only for drag)liftRatio - lift ratio (proportion between 0 and 1 of atmosphere modecules
that will experience specular reflection when hitting spacecraft instead
of experiencing diffuse reflection, hence producing lift)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 BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets, PVCoordinatesProvider sun, double solarArrayArea, Vector3D solarArrayAxis, double dragCoeff, double absorptionCoeff, double reflectionCoeff)
The spacecraft body is described by an array of surface vectors. Each facet of the body is described by a vector normal to the facet (pointing outward of the spacecraft) and whose norm is the surface area in m².
Solar arrays orientation will be such that at each time the Sun direction will always be in the solar array meridian plane defined by solar array rotation axis and solar array normal vector.
facets - body facets (only the facets with strictly positive area will be stored)sun - sun modelsolarArrayArea - area of the solar array (m²)solarArrayAxis - solar array rotation axis in satellite framedragCoeff - 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 BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets, PVCoordinatesProvider sun, double solarArrayArea, Vector3D solarArrayAxis, double dragCoeff, double liftRatio, double absorptionCoeff, double reflectionCoeff)
The spacecraft body is described by an array of surface vectors. Each facet of the body is described by a vector normal to the facet (pointing outward of the spacecraft) and whose norm is the surface area in m².
Solar arrays orientation will be such that at each time the Sun direction will always be in the solar array meridian plane defined by solar array rotation axis and solar array normal vector.
facets - body facets (only the facets with strictly positive area will be stored)sun - sun modelsolarArrayArea - area of the solar array (m²)solarArrayAxis - solar array rotation axis in satellite framedragCoeff - drag coefficient (used only for drag)liftRatio - lift ratio (proportion between 0 and 1 of atmosphere modecules
that will experience specular reflection when hitting spacecraft instead
of experiencing diffuse reflection, hence producing lift)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 BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double absorptionCoeff,
double reflectionCoeff)
Solar arrays orientation will be a regular rotation from the reference orientation at reference date and using a constant rotation rate.
xLength - length of the body along its X axis (m)yLength - length of the body along its Y axis (m)zLength - length of the body along its Z axis (m)sun - sun modelsolarArrayArea - area of the solar array (m²)solarArrayAxis - solar array rotation axis in satellite framereferenceDate - reference date for the solar array rotationreferenceNormal - direction of the solar array normal at reference date
in spacecraft framerotationRate - rotation rate of the solar array, may be 0 (rad/s)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 BoxAndSolarArraySpacecraft(double xLength,
double yLength,
double zLength,
PVCoordinatesProvider sun,
double solarArrayArea,
Vector3D solarArrayAxis,
AbsoluteDate referenceDate,
Vector3D referenceNormal,
double rotationRate,
double dragCoeff,
double liftRatio,
double absorptionCoeff,
double reflectionCoeff)
Solar arrays orientation will be a regular rotation from the reference orientation at reference date and using a constant rotation rate.
xLength - length of the body along its X axis (m)yLength - length of the body along its Y axis (m)zLength - length of the body along its Z axis (m)sun - sun modelsolarArrayArea - area of the solar array (m²)solarArrayAxis - solar array rotation axis in satellite framereferenceDate - reference date for the solar array rotationreferenceNormal - direction of the solar array normal at reference date
in spacecraft framerotationRate - rotation rate of the solar array, may be 0 (rad/s)dragCoeff - drag coefficient (used only for drag)liftRatio - lift ratio (proportion between 0 and 1 of atmosphere modecules
that will experience specular reflection when hitting spacecraft instead
of experiencing diffuse reflection, hence producing lift)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 BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets, PVCoordinatesProvider sun, double solarArrayArea, Vector3D solarArrayAxis, AbsoluteDate referenceDate, Vector3D referenceNormal, double rotationRate, double dragCoeff, double absorptionCoeff, double reflectionCoeff)
The spacecraft body is described by an array of surface vectors. Each facet of the body is described by a vector normal to the facet (pointing outward of the spacecraft) and whose norm is the surface area in m².
Solar arrays orientation will be a regular rotation from the reference orientation at reference date and using a constant rotation rate.
facets - body facets (only the facets with strictly positive area will be stored)sun - sun modelsolarArrayArea - area of the solar array (m²)solarArrayAxis - solar array rotation axis in satellite framereferenceDate - reference date for the solar array rotationreferenceNormal - direction of the solar array normal at reference date
in spacecraft framerotationRate - rotation rate of the solar array, may be 0 (rad/s)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 BoxAndSolarArraySpacecraft(BoxAndSolarArraySpacecraft.Facet[] facets, PVCoordinatesProvider sun, double solarArrayArea, Vector3D solarArrayAxis, AbsoluteDate referenceDate, Vector3D referenceNormal, double rotationRate, double dragCoeff, double liftRatio, double absorptionCoeff, double reflectionCoeff)
The spacecraft body is described by an array of surface vectors. Each facet of the body is described by a vector normal to the facet (pointing outward of the spacecraft) and whose norm is the surface area in m².
Solar arrays orientation will be a regular rotation from the reference orientation at reference date and using a constant rotation rate.
facets - body facets (only the facets with strictly positive area will be stored)sun - sun modelsolarArrayArea - area of the solar array (m²)solarArrayAxis - solar array rotation axis in satellite framereferenceDate - reference date for the solar array rotationreferenceNormal - direction of the solar array normal at reference date
in spacecraft framerotationRate - rotation rate of the solar array, may be 0 (rad/s)dragCoeff - drag coefficient (used only for drag)liftRatio - lift ratio (proportion between 0 and 1 of atmosphere modecules
that will experience specular reflection when hitting spacecraft instead
of experiencing diffuse reflection, hence producing lift)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 ParameterDriver[] getDragParametersDrivers()
getDragParametersDrivers in interface DragSensitivepublic ParameterDriver[] getRadiationParametersDrivers()
getRadiationParametersDrivers in interface RadiationSensitivepublic Vector3D getNormal(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation) 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 frameOrekitException - if sun direction cannot be computed in best lighting
configurationpublic <T extends RealFieldElement<T>> FieldVector3D<T> getNormal(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation) throws OrekitException
T - type of the field elementsdate - 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 frameOrekitException - if sun direction cannot be computed in best lighting
configurationpublic FieldVector3D<DerivativeStructure> getNormal(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldRotation<DerivativeStructure> rotation) 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 frameOrekitException - if sun direction cannot be computed in best lighting
configurationpublic Vector3D dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, double[] parameters) throws OrekitException
The computation includes all spacecraft specific characteristics like shape, area and coefficients.
dragAcceleration in interface DragSensitivedate - 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 parametersOrekitException - if acceleration cannot be computedpublic FieldVector3D<DerivativeStructure> dragAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, double density, Vector3D relativeVelocity, double[] parameters, String paramName) throws OrekitException
dragAcceleration in interface DragSensitivedate - 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 requiredOrekitException - if derivatives cannot be computedpublic Vector3D radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters) throws OrekitException
radiationPressureAcceleration in interface RadiationSensitivedate - 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 computedpublic FieldVector3D<DerivativeStructure> radiationPressureAcceleration(AbsoluteDate date, Frame frame, Vector3D position, Rotation rotation, double mass, Vector3D flux, double[] parameters, String paramName) throws OrekitException
radiationPressureAcceleration in interface RadiationSensitivedate - 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 computedpublic <T extends RealFieldElement<T>> FieldVector3D<T> dragAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, T density, FieldVector3D<T> relativeVelocity, T[] parameters) throws OrekitException
The computation includes all spacecraft specific characteristics like shape, area and coefficients.
dragAcceleration in interface DragSensitiveT - 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 parametersOrekitException - if acceleration cannot be computedpublic <T extends RealFieldElement<T>> FieldVector3D<T> radiationPressureAcceleration(FieldAbsoluteDate<T> date, Frame frame, FieldVector3D<T> position, FieldRotation<T> rotation, T mass, FieldVector3D<T> flux, T[] parameters) throws OrekitException
radiationPressureAcceleration in interface RadiationSensitiveT - 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 computedCopyright © 2002-2018 CS Systèmes d'information. All rights reserved.