public interface DragSensitive
DragForce
Modifier and Type | Field and Description |
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static String |
DRAG_COEFFICIENT
Parameter name for drag coefficient enabling jacobian processing.
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Modifier and Type | Method and Description |
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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)
Compute the acceleration due to drag, with state derivatives.
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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)
Compute the acceleration due to drag.
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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)
Compute acceleration due to drag, with parameters derivatives.
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double |
getDragCoefficient()
Get the drag coefficient.
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void |
setDragCoefficient(double value)
Set the drag coefficient.
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static final String DRAG_COEFFICIENT
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) throws OrekitException
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)OrekitException
- if acceleration cannot be computedorg.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) throws OrekitException
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
- 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)OrekitException
- if acceleration cannot be computedorg.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
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 computedvoid setDragCoefficient(double value)
value
- drag coefficientdouble getDragCoefficient()
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