| Package | Description |
|---|---|
| agi.foundation.coordinates |
Contains types for quantifying and converting between various coordinate representations.
|
| agi.foundation.geometry |
Contains types for expressing the motion of fundamental geometric objects such as points, axes, and reference frames;
the manner in which they are related; and transformations between representations.
|
| agi.foundation.propagators |
Contains types used in producing the state of an object from a known element set.
|
| Modifier and Type | Method and Description |
|---|---|
ModifiedKeplerianElements |
KozaiIzsakMeanElements.toMeanModifiedKeplerianElements()
Returns a mean modified orbit element representation of these mean orbital elements.
|
ModifiedKeplerianElements |
KozaiIzsakMeanElements.toOsculatingModifiedKeplerianElements()
Returns an osculating modified orbit element representation of these mean orbital elements.
|
| Constructor and Description |
|---|
DelaunayElements(ModifiedKeplerianElements elements)
Initialize a set of Delaunay elements based on a set of
ModifiedKeplerianElements. |
EquinoctialElements(ModifiedKeplerianElements elements)
Initialize a set of equinoctial elements from a set of
ModifiedKeplerianElements. |
KeplerianElements(ModifiedKeplerianElements elements)
Initialize a set of classical Keplerian elements from a set of
ModifiedKeplerianElements. |
KozaiIzsakMeanElements(ModifiedKeplerianElements elements,
boolean inputIsMean,
double j2UnnormalizedValue,
double referenceDistance)
Initialize a set of Kozai-Izsak mean elements from a set of osculating or mean
ModifiedKeplerianElements. |
| Modifier and Type | Method and Description |
|---|---|
Evaluator<ModifiedKeplerianElements> |
DynamicModifiedKeplerianElements.getEvaluator()
Gets an evaluator that can be used to compute the
ModifiedKeplerianElements of the
OrbitalPoint (get / set) at a given date. |
Evaluator<ModifiedKeplerianElements> |
DynamicModifiedKeplerianElements.getEvaluator(EvaluatorGroup group)
Gets an evaluator that can be used to compute the
ModifiedKeplerianElements of the
OrbitalPoint (get / set) at a given date. |
| Modifier and Type | Method and Description |
|---|---|
ModifiedKeplerianElements |
J4Propagator.getInitialConditions()
Gets the orbital elements from which to propagate.
|
ModifiedKeplerianElements |
J2Propagator.getInitialConditions()
Gets the orbital elements from which to propagate.
|
ModifiedKeplerianElements |
WalkerConstellation.getSeedElements()
Gets the
ModifiedKeplerianElements of the seed satellite of the Walker constellation. |
| Modifier and Type | Method and Description |
|---|---|
void |
J4Propagator.setInitialConditions(ModifiedKeplerianElements value)
Sets the orbital elements from which to propagate.
|
void |
J2Propagator.setInitialConditions(ModifiedKeplerianElements value)
Sets the orbital elements from which to propagate.
|
void |
WalkerConstellation.setSeedElements(ModifiedKeplerianElements value)
Sets the
ModifiedKeplerianElements of the seed satellite of the Walker constellation. |
| Constructor and Description |
|---|
J2Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
ModifiedKeplerianElements initialConditions,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
|
J4Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
ModifiedKeplerianElements initialConditions,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
|
TwoBodyPropagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
ModifiedKeplerianElements elements)
Initializes a new instance.
|
WalkerConstellation(WalkerConstellationPattern patternType,
boolean phaseByMean,
int numberOfPlanes,
int numberOfSatellitesPerPlane,
int slotOffset,
ModifiedKeplerianElements seedElements)
Creates a Walker constellation from the orbital elements of a seed satellite and other standard Walker constellation input parameters.
|