AbstractGaussianContribution
, DSSTAtmosphericDrag
, DSSTSolarRadiationPressure
, DSSTTesseral
, DSSTThirdBody
, DSSTZonal
public interface DSSTForceModel
DSSTPropagator
.
Objects implementing this interface are intended to be added to a DSST propagator
before the propagation is started.
The propagator will call at the very beginning of a propagation the initialize(AuxiliaryElements, boolean)
method allowing preliminary computation
such as truncation if needed.
Then the propagator will call at each step:
initializeStep(AuxiliaryElements)
method.
The force model instance will extract all the elements needed before
computing the mean element rates.getMeanElementRate(SpacecraftState)
method.
The force model instance will extract all the state data needed to compute
the mean element rates that contribute to the mean state derivative.updateShortPeriodTerms(SpacecraftState...)
method,
if osculating parameters are desired, on a sample of points within the
last step.Modifier and Type | Method | Description |
---|---|---|
EventDetector[] |
getEventsDetectors() |
Get the discrete events related to the model.
|
double[] |
getMeanElementRate(SpacecraftState state) |
Computes the mean equinoctial elements rates dai / dt.
|
List<ShortPeriodTerms> |
initialize(AuxiliaryElements aux,
boolean meanOnly) |
Performs initialization prior to propagation for the current force model.
|
void |
initializeStep(AuxiliaryElements aux) |
Performs initialization at each integration step for the current force model.
|
void |
registerAttitudeProvider(AttitudeProvider provider) |
Register an attitude provider.
|
void |
updateShortPeriodTerms(SpacecraftState... meanStates) |
Update the short period terms.
|
List<ShortPeriodTerms> initialize(AuxiliaryElements aux, boolean meanOnly)
This method aims at being called at the very beginning of a propagation.
aux
- auxiliary elements related to the current orbitmeanOnly
- only mean elements are used during the propagationvoid initializeStep(AuxiliaryElements aux)
This method aims at being called before mean elements rates computation.
aux
- auxiliary elements related to the current orbitdouble[] getMeanElementRate(SpacecraftState state)
state
- current state information: date, kinematics, attitudeEventDetector[] getEventsDetectors()
void registerAttitudeProvider(AttitudeProvider provider)
Register an attitude provider that can be used by the force model.
provider
- the AttitudeProvider
void updateShortPeriodTerms(SpacecraftState... meanStates)
The short period terms
that will be updated
are the ones that were returned during the call to initialize(AuxiliaryElements, boolean)
.
meanStates
- mean states information: date, kinematics, attitudeCopyright © 2002-2019 CS Systèmes d'information. All rights reserved.