KeplerianElementsComputeEccentricAnomaly Method

Computes the eccentric anomaly based on the current Keplerian position.

Namespace: AGI.Foundation.Coordinates
Assembly: AGI.Foundation.Core (in AGI.Foundation.Core.dll) Version: 25.2.423.0 (25.2.423.0)

Syntax

C++

Copy

public double ComputeEccentricAnomaly()

Public Function ComputeEccentricAnomaly As Double

public:
double ComputeEccentricAnomaly()

member ComputeEccentricAnomaly : unit -> float

Return Value

Type: Double
The current eccentric anomaly (radians).

Exceptions

Exception	Condition
InvalidOperationException	Thrown when OrbitType does not represent either a circular or elliptical orbit. To find mean anomaly for parabolic or hyperbolic orbits, convert to ModifiedKeplerianElements.

Remarks

Keplerian elements are not intended to represent parabolic and hyperbolic orbits. To find parabolic and hyperbolic anomalies, convert these elements to ModifiedKeplerianElements.

Reference

KeplerianElements Class

AGI.Foundation.Coordinates Namespace

OrbitalElementsTryConvertTrueAnomalyToEccentricAnomaly(Double, Double, Double)

KeplerianElementsAddLanguageSpecificTextSet("LST8EBC2E24_0?cpp=::|nu=.");ComputeEccentricAnomaly Method

Return Value

Reference

KeplerianElementsComputeEccentricAnomaly Method