| 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.
|
| Constructor and Description |
|---|
DelaunayElements(EquinoctialElements elements)
Initialize a set of Delaunay elements based on a set of
EquinoctialElements. |
KeplerianElements(EquinoctialElements elements)
Initialize a set of classical Keplerian elements from a set of
EquinoctialElements. |
KeplerianElements(EquinoctialElements elements,
double eccentricityTolerance,
double inclinationTolerance)
Initialize a set of classical Keplerian elements from a set of
EquinoctialElements. |
ModifiedKeplerianElements(EquinoctialElements elements)
Initialize a new instance from the given set of
EquinoctialElements. |
ModifiedKeplerianElements(EquinoctialElements elements,
double eccentricityTolerance,
double inclinationTolerance)
Initialize a new instance from the given set of
EquinoctialElements. |
| Modifier and Type | Method and Description |
|---|---|
Evaluator<EquinoctialElements> |
DynamicEquinoctialElements.getEvaluator()
Gets an evaluator that can be used to compute the
EquinoctialElements of the
OrbitalPoint (get / set) at a given date. |
Evaluator<EquinoctialElements> |
DynamicEquinoctialElements.getEvaluator(EvaluatorGroup group)
Gets an evaluator that can be used to compute the
EquinoctialElements of the
OrbitalPoint (get / set) at a given date. |
| Constructor and Description |
|---|
J2Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
EquinoctialElements initialConditions,
double j2UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
|
J4Propagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
EquinoctialElements initialConditions,
double j2UnnormalizedValue,
double j4UnnormalizedValue,
double referenceDistance)
Initializes a new instance.
|
TwoBodyPropagator(JulianDate orbitEpoch,
ReferenceFrame referenceFrame,
EquinoctialElements elements)
Initializes a new instance.
|