Serializable
, BoundedPropagator
, Propagator
, PVCoordinatesProvider
public class Ephemeris extends AbstractAnalyticalPropagator implements BoundedPropagator, Serializable
Modifier and Type | Field | Description |
---|---|---|
static double |
DEFAULT_EXTRAPOLATION_THRESHOLD_SEC |
Default extrapolation time threshold: 1ms.
|
DEFAULT_LAW, DEFAULT_MASS, EPHEMERIS_GENERATION_MODE, MASTER_MODE, SLAVE_MODE
Constructor | Description |
---|---|
Ephemeris(List<SpacecraftState> states,
int interpolationPoints) |
Constructor with tabulated states.
|
Ephemeris(List<SpacecraftState> states,
int interpolationPoints,
double extrapolationThreshold) |
Constructor with tabulated states.
|
Modifier and Type | Method | Description |
---|---|---|
SpacecraftState |
basicPropagate(AbsoluteDate date) |
Propagate an orbit without any fancy features.
|
double |
getExtrapolationThreshold() |
Get the maximum timespan outside of the stored ephemeris that is allowed
for extrapolation.
|
Frame |
getFrame() |
Get the frame in which the orbit is propagated.
|
SpacecraftState |
getInitialState() |
Get the propagator initial state.
|
String[] |
getManagedAdditionalStates() |
Get all the names of all managed states.
|
protected double |
getMass(AbsoluteDate date) |
Get the mass.
|
AbsoluteDate |
getMaxDate() |
Get the last date of the range.
|
AbsoluteDate |
getMinDate() |
Get the first date of the range.
|
TimeStampedPVCoordinates |
getPVCoordinates(AbsoluteDate date,
Frame f) |
Get the
PVCoordinates of the body in the selected frame. |
boolean |
isAdditionalStateManaged(String name) |
Check if an additional state is managed.
|
protected Orbit |
propagateOrbit(AbsoluteDate date) |
Extrapolate an orbit up to a specific target date.
|
void |
resetInitialState(SpacecraftState state) |
Try (and fail) to reset the initial state.
|
protected void |
resetIntermediateState(SpacecraftState state,
boolean forward) |
Reset an intermediate state.
|
acceptStep, addEventDetector, clearEventsDetectors, getEventsDetectors, getGeneratedEphemeris, getPvProvider, propagate
addAdditionalStateProvider, getAdditionalStateProviders, getAttitudeProvider, getFixedStepSize, getMode, getStartDate, getStepHandler, propagate, setAttitudeProvider, setEphemerisMode, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode, setStartDate, updateAdditionalStates
clone, equals, finalize, getClass, hashCode, notify, notifyAll, toString, wait, wait, wait
addAdditionalStateProvider, addEventDetector, clearEventsDetectors, getAdditionalStateProviders, getAttitudeProvider, getEventsDetectors, getGeneratedEphemeris, getMode, propagate, propagate, setAttitudeProvider, setEphemerisMode, setEphemerisMode, setMasterMode, setMasterMode, setSlaveMode
public static final double DEFAULT_EXTRAPOLATION_THRESHOLD_SEC
public Ephemeris(List<SpacecraftState> states, int interpolationPoints) throws org.hipparchus.exception.MathIllegalArgumentException
This constructor allows extrapolating outside of the states time span
by up to the 1ms default
extrapolation threshold
.
states
- tabulates statesinterpolationPoints
- number of points to use in interpolationorg.hipparchus.exception.MathIllegalArgumentException
- if the number of states is smaller than
the number of points to use in interpolationEphemeris(List, int, double)
public Ephemeris(List<SpacecraftState> states, int interpolationPoints, double extrapolationThreshold) throws org.hipparchus.exception.MathIllegalArgumentException
states
- tabulates statesinterpolationPoints
- number of points to use in interpolationextrapolationThreshold
- the largest time difference in seconds between
the start or stop boundary of the ephemeris bounds to be doing extrapolationorg.hipparchus.exception.MathIllegalArgumentException
- if the number of states is smaller than
the number of points to use in interpolationpublic AbsoluteDate getMinDate()
getMinDate
in interface BoundedPropagator
public AbsoluteDate getMaxDate()
getMaxDate
in interface BoundedPropagator
public double getExtrapolationThreshold()
public Frame getFrame()
AbstractPropagator
The propagation frame is the definition frame of the initial state, so this method should be called after this state has been set, otherwise it may return null.
getFrame
in interface Propagator
getFrame
in class AbstractPropagator
Propagator.resetInitialState(SpacecraftState)
public SpacecraftState basicPropagate(AbsoluteDate date)
AbstractAnalyticalPropagator
This method is similar in spirit to the AbstractAnalyticalPropagator.propagate(org.orekit.time.AbsoluteDate, org.orekit.time.AbsoluteDate)
method,
except that it does not call any handler during
propagation, nor any discrete events, not additional states. It always
stop exactly at the specified date.
basicPropagate
in class AbstractAnalyticalPropagator
date
- target date for propagationprotected Orbit propagateOrbit(AbsoluteDate date)
propagateOrbit
in class AbstractAnalyticalPropagator
date
- target date for the orbitprotected double getMass(AbsoluteDate date)
getMass
in class AbstractAnalyticalPropagator
date
- target date for the orbitpublic TimeStampedPVCoordinates getPVCoordinates(AbsoluteDate date, Frame f)
PVCoordinates
of the body in the selected frame.getPVCoordinates
in interface PVCoordinatesProvider
getPVCoordinates
in class AbstractPropagator
date
- current datef
- the frame where to define the positionpublic void resetInitialState(SpacecraftState state)
This method always throws an exception, as ephemerides cannot be reset.
resetInitialState
in interface Propagator
resetInitialState
in class AbstractPropagator
state
- new initial state to considerprotected void resetIntermediateState(SpacecraftState state, boolean forward)
resetIntermediateState
in class AbstractAnalyticalPropagator
state
- new intermediate state to considerforward
- if true, the intermediate state is valid for
propagations after itselfpublic SpacecraftState getInitialState()
getInitialState
in interface Propagator
getInitialState
in class AbstractPropagator
public boolean isAdditionalStateManaged(String name)
Managed states are states for which the propagators know how to compute
its evolution. They correspond to additional states for which an
additional state provider
has been registered
by calling the addAdditionalStateProvider
method. If the propagator is an integrator-based
propagator
, the states for which a set of additional equations
has
been registered by calling the addAdditionalEquations
method are also counted as managed additional states.
Additional states that are present in the initial state
but have no evolution method registered are not considered as managed states.
These unmanaged additional states are not lost during propagation, though. Their
value will simply be copied unchanged throughout propagation.
isAdditionalStateManaged
in interface Propagator
isAdditionalStateManaged
in class AbstractPropagator
name
- name of the additional statepublic String[] getManagedAdditionalStates()
getManagedAdditionalStates
in interface Propagator
getManagedAdditionalStates
in class AbstractPropagator
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