KozaiIzsakMeanElements Class

A set of Kozai-Izsak mean elements representing an elliptical orbit.

For more information see the paper, "The Motion of a Close Earth Satellite", Y.Kozai, 1959.

Inheritance Hierarchy

SystemObject
AGI.Foundation.CoordinatesKozaiIzsakMeanElements

Namespace: AGI.Foundation.Coordinates
Assembly: AGI.Foundation.Core (in AGI.Foundation.Core.dll) Version: 24.3.420.0 (24.3.420.0)

Syntax

public sealed class KozaiIzsakMeanElements : ICloneWithContext

Public NotInheritable Class KozaiIzsakMeanElements
	Implements ICloneWithContext

public ref class KozaiIzsakMeanElements sealed : ICloneWithContext

[<SealedAttribute>]
type KozaiIzsakMeanElements =  
    class
        interface ICloneWithContext
    end

The KozaiIzsakMeanElements type exposes the following members.

Constructors

	Name	Description
	KozaiIzsakMeanElements(KeplerianElements, Boolean, Double, Double)	Initialize a set of Kozai-Izsak mean elements from a set of osculating or mean KeplerianElements.
	KozaiIzsakMeanElements(ModifiedKeplerianElements, Boolean, Double, Double)	Initialize a set of Kozai-Izsak mean elements from a set of osculating or mean ModifiedKeplerianElements.
	KozaiIzsakMeanElements(MotionCartesian, Double, Double, Double)	Initializes a set of Kozai-Izsak mean elements from the specified Cartesian motion. Please note that there must be a correspondence between the inertial and fixed frames used for the input motion. Specifically, the XY plane of the input motion should correspond to the equatorial plane.
	KozaiIzsakMeanElements(Cartesian, Cartesian, Double, Double, Double)	Initialize a set of Kozai-Izsak mean elements from a Cartesian position and velocity. Please note that there must be a correspondence between the inertial and fixed frames used for the input position and velocity. Specifically, the XY plane of the input motion should correspond to the equatorial plane.
	KozaiIzsakMeanElements(Double, Double, Double, Double, Double, Double, Double, Double, Double)	Initialize a set of Kozai-Izsak mean orbital elements. Inputs are assumed to be mean elements.

Properties

	Name	Description
	ArgumentOfLatitude	Gets the argument of latitude of the orbit (radians).
	GravitationalParameter	Gets the gravitational parameter used for this element set (distance cubed per time squared).
	Inclination	Gets the inclination of the orbit, in radians.
	J2ZonalHarmonicCoefficient	Gets the unnormalized J2 zonal harmonic coefficient used for this element set.
	OrbitType	Gets the type of orbit represented by these elements.
	RadialVelocity	Gets the rate of change of the magnitude of the position vector (distance/time).
	Radius	Gets the magnitude of the position vector (distance).
	ReferenceDistance	Gets the reference distance (equatorial radius) associated with the J2 zonal harmonic coefficient.
	RightAscensionOfAscendingNode	Gets the right ascension of the ascending node of the orbit, in radians.
	SemilatusRectum	Gets the semi-latus rectum of the orbit (distance).

Methods

	Name	Description
	Clone	Clones this object using the specified context.
	ComputeEccentricAnomaly	Computes the mean eccentric anomaly.
	ComputeEccentricity	Computes the mean eccentricity of the orbit.
	ComputeMeanAnomaly	Computes the mean mean anomaly.
	ComputeOsculatingRadiusOfApoapsis	Computes the osculating radius of apoapsis.
	ComputeOsculatingRadiusOfPeriapsis	Computes the osculating radius of periapsis.
	ComputeSemimajorAxis	Computes the mean semi-major axis length of the orbit.
	ComputeTrueAnomaly	Computes the mean true anomaly.
	Equals	Determines whether the specified object is equal to the current object. (Inherited from Object.)
	GetHashCode	Serves as the default hash function. (Inherited from Object.)
	GetType	Gets the Type of the current instance. (Inherited from Object.)
	ToCartesian	Returns an osculating Cartesian representation of these mean orbital elements.
	ToMeanKeplerianElements	Returns a mean Keplerian orbit element representation of these mean orbital elements.
	ToMeanModifiedKeplerianElements	Returns a mean modified orbit element representation of these mean orbital elements.
	ToOsculatingKeplerianElements	Returns an osculating Keplerian orbit element representation of these mean orbital elements.
	ToOsculatingModifiedKeplerianElements	Returns an osculating modified orbit element representation of these mean orbital elements.
	ToString	Returns a string that represents the current object. (Inherited from Object.)

Remarks

This class is meant to represent classical circular and elliptical orbits.