public class DSSTPartialDerivativesEquations extends Object implements AdditionalEquations
additional equations computing the partial derivatives
of the state (orbit) with respect to initial state and force models parameters.
This set of equations are automatically added to a DSST propagator
in order to compute partial derivatives of the orbit along with the orbit itself. This is
useful for example in orbit determination applications.
The partial derivatives with respect to initial state are dimension 6 (orbit only).
The partial derivatives with respect to force models parameters has a dimension
equal to the number of selected parameters. Parameters selection is implemented at
DSST force models level. Users must retrieve a parameter driver by looping on all drivers using DSSTForceModel.getParametersDrivers()
and then select it by calling setSelected(true).
| Constructor and Description |
|---|
DSSTPartialDerivativesEquations(String name,
DSSTPropagator propagator,
PropagationType propagationType)
Simple constructor.
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| Modifier and Type | Method and Description |
|---|---|
double[] |
computeDerivatives(SpacecraftState s,
double[] pDot)
Compute the derivatives related to the additional state parameters.
|
DSSTJacobiansMapper |
getMapper()
Get a mapper between two-dimensional Jacobians and one-dimensional additional state.
|
String |
getName()
Get the name of the additional state.
|
ParameterDriversList |
getSelectedParameters()
Get the selected parameters, in Jacobian matrix column order.
|
SpacecraftState |
setInitialJacobians(SpacecraftState s0)
Set the initial value of the Jacobian with respect to state and parameter.
|
SpacecraftState |
setInitialJacobians(SpacecraftState s1,
double[][] dY1dY0,
double[][] dY1dP)
Set the initial value of the Jacobian with respect to state and parameter.
|
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, waitinitpublic DSSTPartialDerivativesEquations(String name, DSSTPropagator propagator, PropagationType propagationType)
Upon construction, this set of equations is automatically added to
the propagator by calling its AbstractIntegratedPropagator.addAdditionalEquations(AdditionalEquations) method. So
there is no need to call this method explicitly for these equations.
name - name of the partial derivatives equationspropagator - the propagator that will handle the orbit propagationpropagationType - type of the orbit used for the propagation (mean or osculating)public String getName()
getName in interface AdditionalEquationspublic SpacecraftState setInitialJacobians(SpacecraftState s0)
This method is equivalent to call setInitialJacobians(SpacecraftState,
double[][], double[][]) with dYdY0 set to the identity matrix and dYdP set
to a zero matrix.
The force models parameters for which partial derivatives are desired,
must have been selected
before this method is called, so proper matrices dimensions are used.
s0 - initial stategetSelectedParameters()public SpacecraftState setInitialJacobians(SpacecraftState s1, double[][] dY1dY0, double[][] dY1dP)
The returned state must be added to the propagator (it is not done automatically, as the user may need to add more states to it).
The force models parameters for which partial derivatives are desired,
must have been selected
before this method is called, and the dY1dP matrix dimension must
be consistent with the selection.
s1 - current statedY1dY0 - Jacobian of current state at time t₁ with respect
to state at some previous time t₀ (must be 6x6)dY1dP - Jacobian of current state at time t₁ with respect
to parameters (may be null if no parameters are selected)getSelectedParameters()public DSSTJacobiansMapper getMapper()
setInitialJacobians(SpacecraftState),
setInitialJacobians(SpacecraftState, double[][], double[][])public ParameterDriversList getSelectedParameters()
The force models parameters for which partial derivatives are desired,
must have been selected
before this method is called, so the proper list is returned.
public double[] computeDerivatives(SpacecraftState s, double[] pDot)
When this method is called, the spacecraft state contains the main
state (orbit, attitude and mass), all the states provided through
the additional
state providers registered to the propagator, and the additional state
integrated using this equation. It does not contains any other
states to be integrated alongside during the same propagation.
computeDerivatives in interface AdditionalEquationss - current state information: date, kinematics, attitude, and
additional statepDot - placeholder where the derivatives of the additional parameters
should be putCopyright © 2002-2020 CS Group. All rights reserved.