Package | Description |
---|---|
org.orekit.propagation.conversion |
This package provides tools to convert a given propagator or a set of
SpacecraftState into another propagator. |
org.orekit.propagation.semianalytical.dsst |
This package provides an implementation of the Draper Semi-analytical
Satellite Theory (DSST).
|
org.orekit.propagation.semianalytical.dsst.forces |
This package provides force models for Draper Semi-analytical Satellite Theory (DSST).
|
Modifier and Type | Method and Description |
---|---|
List<DSSTForceModel> |
DSSTPropagatorBuilder.getAllForceModels()
Get the list of all force models.
|
Modifier and Type | Method and Description |
---|---|
void |
DSSTPropagatorBuilder.addForceModel(DSSTForceModel model)
Add a force model to the global perturbation model.
|
Modifier and Type | Method and Description |
---|---|
List<DSSTForceModel> |
FieldDSSTPropagator.getAllForceModels()
Get all the force models, perturbing forces and Newtonian attraction included.
|
List<DSSTForceModel> |
DSSTPropagator.getAllForceModels()
Get all the force models, perturbing forces and Newtonian attraction included.
|
Modifier and Type | Method and Description |
---|---|
void |
FieldDSSTPropagator.addForceModel(DSSTForceModel force)
Add a force model to the global perturbation model.
|
void |
DSSTPropagator.addForceModel(DSSTForceModel force)
Add a force model to the global perturbation model.
|
Modifier and Type | Method and Description |
---|---|
static <T extends org.hipparchus.CalculusFieldElement<T>> |
FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating,
AttitudeProvider attitudeProvider,
Collection<DSSTForceModel> forceModel)
Conversion from osculating to mean orbit.
|
static <T extends org.hipparchus.CalculusFieldElement<T>> |
FieldDSSTPropagator.computeMeanState(FieldSpacecraftState<T> osculating,
AttitudeProvider attitudeProvider,
Collection<DSSTForceModel> forceModel,
double epsilon,
int maxIterations)
Conversion from osculating to mean orbit.
|
static SpacecraftState |
DSSTPropagator.computeMeanState(SpacecraftState osculating,
AttitudeProvider attitudeProvider,
Collection<DSSTForceModel> forceModels)
Conversion from osculating to mean orbit.
|
static SpacecraftState |
DSSTPropagator.computeMeanState(SpacecraftState osculating,
AttitudeProvider attitudeProvider,
Collection<DSSTForceModel> forceModels,
double epsilon,
int maxIterations)
Conversion from osculating to mean orbit.
|
static <T extends org.hipparchus.CalculusFieldElement<T>> |
FieldDSSTPropagator.computeOsculatingState(FieldSpacecraftState<T> mean,
AttitudeProvider attitudeProvider,
Collection<DSSTForceModel> forces)
Conversion from mean to osculating orbit.
|
static SpacecraftState |
DSSTPropagator.computeOsculatingState(SpacecraftState mean,
AttitudeProvider attitudeProvider,
Collection<DSSTForceModel> forces)
Conversion from mean to osculating orbit.
|
Modifier and Type | Class and Description |
---|---|
class |
AbstractGaussianContribution
Common handling of
DSSTForceModel methods for Gaussian contributions
to DSST propagation. |
class |
DSSTAtmosphericDrag
Atmospheric drag contribution to the
DSSTPropagator . |
class |
DSSTJ2SquaredClosedForm
Second order J2-squared force model.
|
class |
DSSTNewtonianAttraction
Force model for Newtonian central body attraction for the
DSST propagator . |
class |
DSSTSolarRadiationPressure
Solar radiation pressure contribution to the
DSSTPropagator . |
class |
DSSTTesseral
Tesseral contribution to the central body gravitational perturbation.
|
class |
DSSTThirdBody
Third body attraction perturbation to the
DSSTPropagator . |
class |
DSSTZonal
Zonal contribution to the central body gravitational perturbation.
|
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