public class NewtonianAttraction extends AbstractForceModel
Modifier and Type | Field and Description |
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static String |
CENTRAL_ATTRACTION_COEFFICIENT
Name of the single parameter of this model: the central attraction coefficient.
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Constructor and Description |
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NewtonianAttraction(double mu)
Simple constructor.
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Modifier and Type | Method and Description |
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FieldVector3D<DerivativeStructure> |
accelerationDerivatives(AbsoluteDate date,
Frame frame,
FieldVector3D<DerivativeStructure> position,
FieldVector3D<DerivativeStructure> velocity,
FieldRotation<DerivativeStructure> rotation,
DerivativeStructure mass)
Compute acceleration derivatives with respect to state parameters.
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FieldVector3D<DerivativeStructure> |
accelerationDerivatives(SpacecraftState s,
String paramName)
Compute acceleration derivatives with respect to additional parameters.
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void |
addContribution(SpacecraftState s,
TimeDerivativesEquations adder)
Compute the contribution of the force model to the perturbing
acceleration.
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EventDetector[] |
getEventsDetectors()
Get the discrete events related to the model.
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double |
getMu()
Get the central attraction coefficient μ.
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ParameterDriver[] |
getParametersDrivers()
Get the drivers for force model parameters.
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complainIfNotSupported, getParameter, getParameterDriver, getParametersNames, isSupported, setParameter
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
init
public static final String CENTRAL_ATTRACTION_COEFFICIENT
public NewtonianAttraction(double mu)
mu
- central attraction coefficient (m^3/s^2)public FieldVector3D<DerivativeStructure> accelerationDerivatives(AbsoluteDate date, Frame frame, FieldVector3D<DerivativeStructure> position, FieldVector3D<DerivativeStructure> velocity, FieldRotation<DerivativeStructure> rotation, DerivativeStructure mass) throws OrekitException
The derivatives should be computed with respect to position, velocity and optionnaly mass. The input parameters already take into account the free parameters (6 or 7 depending on derivation with respect to mass being considered or not) and order (always 1). Free parameters at indices 0, 1 and 2 correspond to derivatives with respect to position. Free parameters at indices 3, 4 and 5 correspond to derivatives with respect to velocity. Free parameter at index 6 (if present) corresponds to to derivatives with respect to mass.
date
- current dateframe
- inertial reference frame for state (both orbit and attitude)position
- position of spacecraft in reference framevelocity
- velocity of spacecraft in reference framerotation
- orientation (attitude) of the spacecraft with respect to reference framemass
- spacecraft massOrekitException
- if derivatives cannot be computedpublic FieldVector3D<DerivativeStructure> accelerationDerivatives(SpacecraftState s, String paramName) throws OrekitException
s
- spacecraft stateparamName
- name of the parameter with respect to which derivatives are requiredOrekitException
- if derivatives cannot be computedpublic double getMu()
public void addContribution(SpacecraftState s, TimeDerivativesEquations adder) throws OrekitException
s
- current state information: date, kinematics, attitudeadder
- object where the contribution should be addedOrekitException
- if some specific error occurspublic EventDetector[] getEventsDetectors()
public ParameterDriver[] getParametersDrivers()
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