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LifetimeElements Constructor

Initialize a set of lifetime orbit elements to represent one orbit pass.

Namespace:  AGI.Foundation.Coordinates
Assembly:  AGI.Foundation.OrbitPropagation (in AGI.Foundation.OrbitPropagation.dll) Version: 19.1.398.0 (19.1.398.0)
Syntax
public LifetimeElements(
	JulianDate epoch,
	int orbitCount,
	double semimajorAxis,
	double semimajorAxisRate,
	double eccentricity,
	double eccentricityRate,
	double inclination,
	double inclinationRate,
	double argumentOfPeriapsis,
	double argumentOfPeriapsisRate,
	double rightAscensionOfAscendingNode,
	double rightAscensionOfAscendingNodeRate,
	double siderealPeriod,
	double gravitationalParameter
)

Parameters

epoch
Type: AGI.Foundation.TimeJulianDate
The time at periapsis.
orbitCount
Type: SystemInt32
The number of orbits, including this one, since the reference epoch.
semimajorAxis
Type: SystemDouble
Semimajor axis, in meters.
semimajorAxisRate
Type: SystemDouble
The rate of change of the semimajor axis, in meters per second.
eccentricity
Type: SystemDouble
Eccentricity.
eccentricityRate
Type: SystemDouble
The rate of change of the eccentricity, in units per second.
inclination
Type: SystemDouble
Inclination, in radians.
inclinationRate
Type: SystemDouble
The rate of change of the inclination, in radians per second.
argumentOfPeriapsis
Type: SystemDouble
Argument of periapsis, in radians.
argumentOfPeriapsisRate
Type: SystemDouble
The rate of change of the argument of periapsis, in radians per second.
rightAscensionOfAscendingNode
Type: SystemDouble
Right ascension of the ascending node, in radians.
rightAscensionOfAscendingNodeRate
Type: SystemDouble
The rate of change of the right ascension of the ascending node, in radians per second.
siderealPeriod
Type: SystemDouble
The time required to make one full orbit with respect to inertial space, in seconds.
gravitationalParameter
Type: SystemDouble
Gravitational parameter (meters cubed per second 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