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KeplerianElements Constructor (Double, Double, Double, Double, Double, Double, Double)

Initialize a set of classical Keplerian orbital elements.

Namespace:  AGI.Foundation.Coordinates
Assembly:  AGI.Foundation.Core (in AGI.Foundation.Core.dll) Version: 19.1.398.0 (19.1.398.0)
Syntax
public KeplerianElements(
	double semimajorAxis,
	double eccentricity,
	double inclination,
	double argumentOfPeriapsis,
	double rightAscensionOfAscendingNode,
	double trueAnomaly,
	double gravitationalParameter
)

Parameters

semimajorAxis
Type: SystemDouble
Semimajor axis (distance).
eccentricity
Type: SystemDouble
Eccentricity.
inclination
Type: SystemDouble
Inclination (radians).
argumentOfPeriapsis
Type: SystemDouble
Argument of periapsis (radians).
rightAscensionOfAscendingNode
Type: SystemDouble
Right ascension of the ascending node (radians).
trueAnomaly
Type: SystemDouble
True anomaly (radians).
gravitationalParameter
Type: SystemDouble
Gravitational parameter (distance cubed per time squared).
Exceptions
ExceptionCondition
ArgumentOutOfRangeExceptionThe given elements must represent a closed orbit. The exception is thrown if the eccentricity is negative, not below unity, or if the semimajor axis is not finitely positive. For other orbit types, use ModifiedKeplerianElements.
ArgumentOutOfRangeExceptionThe semimajor axis cannot be zero or nearly zero. Thrown if semimajorAxis is < Epsilon8.
ArgumentOutOfRangeExceptionThrown if the inclination is less than zero or greater than Pi radians.
Remarks
The classification of the OrbitType is exact so that if the user wants this instance of KeplerianElements to be classified as a Circular orbit, the eccentricity must be exactly zero. For parabolic or hyperbolic orbits, see ModifiedKeplerianElements.
See Also