@Deprecated public class DSSTPartialDerivativesEquations extends Object implements AdditionalDerivativesProvider, AdditionalEquations
derivatives provider
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 ParametersDriversProvider.getParametersDrivers()
and then select it by calling setSelected(true)
.
Constructor and Description 

DSSTPartialDerivativesEquations(String name,
DSSTPropagator propagator,
PropagationType propagationType)
Deprecated.
Simple constructor.

Modifier and Type  Method and Description 

CombinedDerivatives 
combinedDerivatives(SpacecraftState s)
Deprecated.
Compute the derivatives related to the additional state (and optionally main state increments).

double[] 
computeDerivatives(SpacecraftState s,
double[] pDot)
Deprecated.
Compute the derivatives related to the additional state parameters.

double[] 
derivatives(SpacecraftState state)
Deprecated.

int 
getDimension()
Deprecated.
Get the dimension of the generated derivative.

DSSTJacobiansMapper 
getMapper()
Deprecated.
Get a mapper between twodimensional Jacobians and onedimensional additional state.

String 
getName()
Deprecated.
Get the name of the additional derivatives (which will become state once integrated).

void 
init(SpacecraftState initialState,
AbsoluteDate target)
Deprecated.
Initialize the generator at the start of propagation.

SpacecraftState 
setInitialJacobians(SpacecraftState s0)
Deprecated.
Set the initial value of the Jacobian with respect to state and parameter.

SpacecraftState 
setInitialJacobians(SpacecraftState s1,
double[][] dY1dY0,
double[][] dY1dP)
Deprecated.
Set the initial value of the Jacobian with respect to state and parameter.

clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
yield
public DSSTPartialDerivativesEquations(String name, DSSTPropagator propagator, PropagationType propagationType)
Upon construction, this set of equations is automatically added to
the propagator by calling its AbstractIntegratedPropagator.addAdditionalDerivativesProvider(AdditionalDerivativesProvider)
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 AdditionalDerivativesProvider
getName
in interface AdditionalEquations
public int getDimension()
getDimension
in interface AdditionalDerivativesProvider
public 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 statepublic 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)public DSSTJacobiansMapper getMapper()
setInitialJacobians(SpacecraftState)
,
setInitialJacobians(SpacecraftState, double[][], double[][])
public void init(SpacecraftState initialState, AbsoluteDate target)
init
in interface AdditionalDerivativesProvider
init
in interface AdditionalEquations
initialState
 initial state information at the start of propagationtarget
 date of propagationpublic 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 AdditionalEquations
s
 current state information: date, kinematics, attitude, and
additional statepDot
 placeholder where the derivatives of the additional parameters
should be put@Deprecated public double[] derivatives(SpacecraftState state)
derivatives
in interface AdditionalDerivativesProvider
state
 current state information: date, kinematics, attitude, and
additional states this equations depend on (according to the
yield
method)public CombinedDerivatives combinedDerivatives(SpacecraftState s)
As of 11.2, there is a default implementation that calls the deprecated
AdditionalDerivativesProvider.derivatives(SpacecraftState)
method. This has been done for
backward compatibility only and will be removed in 12.0.
combinedDerivatives
in interface AdditionalDerivativesProvider
s
 current state information: date, kinematics, attitude, and
additional states this equations depend on (according to the
yield
method)Copyright © 20022022 CS GROUP. All rights reserved.