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java.lang.Object org.orekit.parameter.Parameterizable org.orekit.parameter.JacobiansParameterizable org.orekit.forces.gravity.NewtonianAttraction
public class NewtonianAttraction
Force model for Newtonian central body attraction.
The implementation of this class enables the computation of partial derivatives with respect to the central attraction coefficient.
Field Summary |
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Fields inherited from interface org.orekit.forces.gravity.AttractionModel |
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MU |
Constructor Summary | |
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NewtonianAttraction(double mu)
Simple constructor. |
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NewtonianAttraction(double mu,
boolean computePD)
Simple constructor. |
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NewtonianAttraction(Parameter mu)
Simple constructor using Parameter . |
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NewtonianAttraction(Parameter mu,
boolean computePD)
Simple constructor using Parameter . |
Method Summary | |
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void |
addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing acceleration. |
void |
addDAccDParam(SpacecraftState s,
Parameter param,
double[] dAccdParam)
Compute acceleration derivatives with respect to additional parameters. |
void |
addDAccDState(SpacecraftState s,
double[][] dAccdPos,
double[][] dAccdVel)
Compute acceleration derivatives with respect to state parameters. |
Vector3D |
computeAcceleration(PVCoordinates pv,
Frame frame,
AbsoluteDate date)
Method to compute the acceleration. |
Vector3D |
computeAcceleration(SpacecraftState s)
Compute the acceleration due to the force. |
boolean |
computeGradientPosition()
This method returns true if the acceleration partial derivatives with respect to position have to be computed. |
boolean |
computeGradientVelocity()
This method returns true if the acceleration partial derivatives with respect to velocity have to be computed. |
EventDetector[] |
getEventsDetectors()
Get the discrete events related to the model. |
double |
getMu()
Get the central attraction coefficient &mu. |
Methods inherited from class org.orekit.parameter.JacobiansParameterizable |
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addJacobiansParameter, addJacobiansParameter, addJacobiansParameter, supportsJacobianParameter |
Methods inherited from class org.orekit.parameter.Parameterizable |
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addParameter, getParameters, supportsParameter |
Methods inherited from class java.lang.Object |
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clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait |
Methods inherited from interface org.orekit.parameter.IParameterizable |
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getParameters, supportsParameter |
Constructor Detail |
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public NewtonianAttraction(double mu)
mu
- central attraction coefficient (m^3/s^2)public NewtonianAttraction(double mu, boolean computePD)
mu
- central attraction coefficient (m^3/s^2)computePD
- true if partial derivatives wrt position have to be computedpublic NewtonianAttraction(Parameter mu)
Parameter
.
mu
- parameter representing central attraction coefficient (m^3/s^2)public NewtonianAttraction(Parameter mu, boolean computePD)
Parameter
.
mu
- parameter representing central attraction coefficient (m^3/s^2)computePD
- true if partial derivatives wrt position have to be computedMethod Detail |
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public void addContribution(SpacecraftState s, TimeDerivativesEquations adder) throws OrekitException
addContribution
in interface ForceModel
s
- current state information: date, kinematics, attitudeadder
- object where the contribution should be added
OrekitException
- if some specific error occurspublic EventDetector[] getEventsDetectors()
getEventsDetectors
in interface ForceModel
public double getMu()
getMu
in interface AttractionModel
public boolean computeGradientPosition()
computeGradientPosition
in interface GradientModel
public boolean computeGradientVelocity()
computeGradientVelocity
in interface GradientModel
public Vector3D computeAcceleration(SpacecraftState s) throws OrekitException
computeAcceleration
in interface ForceModel
s
- current state information: date, kinematics, attitude
SpacecraftState frame
OrekitException
- if some specific error occurspublic Vector3D computeAcceleration(PVCoordinates pv, Frame frame, AbsoluteDate date) throws OrekitException
Method to compute the acceleration. This method has been implemented in order to validate the force model only. The reason is that for the validation context, we do not want to set up an instance of the SpacecraftState object to avoid the inertial frame of the spacecraft orbit.
(see Story #V82 and Feature #34 on https://www.orekit.org/forge/issues/34)
Out of the validation context, one must use the method Vector3D computeAcceleration(final SpacecraftState s)
pv
- PV coordinates of the spacecraftframe
- frame in which the acceleration is computeddate
- date
OrekitException
- if an Orekit error occurspublic void addDAccDState(SpacecraftState s, double[][] dAccdPos, double[][] dAccdVel) throws OrekitException
addDAccDState
in interface IJacobiansParameterizable
s
- spacecraft statedAccdPos
- acceleration derivatives with respect to positiondAccdVel
- acceleration derivatives with respect to velocity
OrekitException
- if derivatives cannot be computedpublic void addDAccDParam(SpacecraftState s, Parameter param, double[] dAccdParam) throws OrekitException
AttractionModel.MU
--> derivatives with respect to the central attraction coefficient
addDAccDParam
in interface IJacobiansParameterizable
s
- spacecraft stateparam
- the parameter with respect to which derivatives are requireddAccdParam
- acceleration derivatives with respect to specified parameters
OrekitException
- if derivatives cannot be computed
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