Click or drag to resize

KeplerianElementsComputeTimeOfFlight Method

Note: This API is now obsolete.

Computes the time of flight between the two true anomalies.

Namespace:  AGI.Foundation.Coordinates
Assembly:  AGI.Foundation.Core (in AGI.Foundation.Core.dll) Version: 19.1.398.0 (19.1.398.0)
Syntax
[ObsoleteAttribute("Use OrbitalElements.TryComputeTimeOfFlight instead.")]
public static double ComputeTimeOfFlight(
	double initialTrueAnomaly,
	double finalTrueAnomaly,
	double semimajorAxis,
	double eccentricity,
	double gravitationalParameter
)

Parameters

initialTrueAnomaly
Type: SystemDouble
The initial true anomaly (radians).
finalTrueAnomaly
Type: SystemDouble
The final true anomaly (radians).
semimajorAxis
Type: SystemDouble
The semimajor axis (distance).
eccentricity
Type: SystemDouble
The eccentricity.
gravitationalParameter
Type: SystemDouble
The gravitational parameter (distance cubed per time squared).

Return Value

Type: Double
The time of flight (time).
Exceptions
ExceptionCondition
ArgumentOutOfRangeException The eccentricity and semimajor axis must represent an elliptical orbit when using this method. For computing time of flight with parabolic and hyperbolic orbits, use instance methods.
See Also