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KeplerianElements Class

A set of classical Keplerian elements representing an elliptical orbit.

All units are SI unless indicated otherwise. For more information see the Units topic.

Inheritance Hierarchy
SystemObject
  AGI.Foundation.CoordinatesKeplerianElements

Namespace:  AGI.Foundation.Coordinates
Assembly:  AGI.Foundation.Core (in AGI.Foundation.Core.dll) Version: 19.1.398.0 (19.1.398.0)
Syntax
public sealed class KeplerianElements : ICloneWithContext

The KeplerianElements type exposes the following members.

Constructors
  NameDescription
Public methodKeplerianElements(DelaunayElements)
Initialize a set of classical Keplerian elements from a set of DelaunayElements.
Public methodKeplerianElements(EquinoctialElements)
Initialize a set of classical Keplerian elements from a set of EquinoctialElements.
Public methodKeplerianElements(ModifiedKeplerianElements)
Initialize a set of classical Keplerian elements from a set of ModifiedKeplerianElements.
Public methodKeplerianElements(MotionCartesian, Double)
Initializes a new instance from the specified cartesian motion and gravitational constant.
Public methodKeplerianElements(Cartesian, Cartesian, Double)
Initialize a set of classical Keplerian elements from a cartesian position and velocity.
Public methodKeplerianElements(DelaunayElements, Double, Double)
Initialize a set of classical Keplerian elements from a set of DelaunayElements.
Public methodKeplerianElements(EquinoctialElements, Double, Double)
Initialize a set of classical Keplerian elements from a set of EquinoctialElements.
Public methodKeplerianElements(MotionCartesian, Double, Double, Double)
Initializes a new instance from the specified cartesian motion and gravitational constant.
Public methodKeplerianElements(Cartesian, Cartesian, Double, Double, Double)
Initialize a set of classical Keplerian elements from a cartesian position and velocity.
Public methodKeplerianElements(Double, Double, Double, Double, Double, Double, Double)
Initialize a set of classical Keplerian orbital elements.
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Properties
  NameDescription
Public propertyArgumentOfPeriapsis
Gets the argument of periapsis of the orbit, in radians.
Public propertyEccentricity
Gets the eccentricity of the orbit.
Public propertyGravitationalParameter
Gets the gravitational parameter used for this element set (distance cubed per time squared).
Public propertyInclination
Gets the inclination of the orbit, in radians.
Public propertyOrbitType
Gets the type of orbit represented by these elements.
Public propertyRightAscensionOfAscendingNode
Gets the right ascension of the ascending node of the orbit, in radians.
Public propertySemimajorAxis
Gets the semimajor axis of the orbit (distance).
Public propertyTrueAnomaly
Gets the true anomaly of the orbit, in radians.
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Methods
  NameDescription
Public methodClone
Clones this object using the specified context.
Public methodComputeEccentricAnomaly
Computes the eccentric anomaly based on the current Keplerian position.
Public methodStatic memberComputeEccentricity Obsolete.
Computes the eccentricity from the given radius of periapsis and the semimajor axis.
Public methodComputeMeanAnomaly
Computes the Mean anomaly based on the current Keplerian position.
Public methodComputeMeanMotion
Computes the mean motion based on the current Keplerian elements.
Public methodComputePeriod
Computes the orbital period of the current Keplerian elements.
Public methodComputeRadiusOfApoapsis
Computes the apoapsis of the current Keplerian elements.
Public methodStatic memberComputeRadiusOfApoapsis(Double, Double) Obsolete.
Computes the radius of apoapsis.
Public methodComputeRadiusOfPeriapsis
Computes the periapsis of the current Keplerian elements.
Public methodStatic memberComputeRadiusOfPeriapsis(Double, Double) Obsolete.
Computes the radius of periapsis.
Public methodComputeSemilatusRectum
Computes the semilatus rectum of the current Keplerian elements.
Public methodStatic memberComputeTimeOfFlight Obsolete.
Computes the time of flight between the two true anomalies.
Public methodStatic memberComputeTimePastPeriapsis(Double, Double, Double) Obsolete.
Computes the time of flight since the last periapsis passage.
Public methodStatic memberComputeTimePastPeriapsis(Double, Double, Double, Double) Obsolete.
Computes the time of flight since the last periapsis passage.
Public methodStatic memberEccentricAnomalyToMeanAnomaly Obsolete.
Calculates the mean anomaly given the eccentric anomaly and the eccentricity.
Public methodStatic memberEccentricAnomalyToTrueAnomaly Obsolete.
Calculates the true anomaly given the eccentric anomaly and the eccentricity.
Public methodEquals
Determines whether the specified object is equal to the current object.
(Inherited from Object.)
Public methodGetHashCode
Serves as the default hash function.
(Inherited from Object.)
Public methodGetType
Gets the Type of the current instance.
(Inherited from Object.)
Public methodStatic memberMeanAnomalyToEccentricAnomaly Obsolete.
Calculates the eccentric anomaly given the mean anomaly and the eccentricity.
Public methodStatic memberMeanAnomalyToTrueAnomaly Obsolete.
Calculates the true anomaly given the mean anomaly and the eccentricity.
Public methodStatic memberPerifocalToCartesianMatrix Obsolete.
Calculates the transformation matrix to convert from the perifocal (PQW) coordinate system to inertial cartesian coordinates.
Public methodStatic memberSemimajorAxisToPeriod Obsolete.
Calculates the orbital period from the semimajor axis and gravitational parameter.
Public methodStatic memberTimePastPeriapsisToEccentricAnomaly Obsolete.
Calculates the eccentric anomaly given the time past the last periapsis passage.
Public methodStatic memberTimePastPeriapsisToMeanAnomaly Obsolete.
Calculates the mean anomaly given the time past the last periapsis passage.
Public methodStatic memberTimePastPeriapsisToTrueAnomaly Obsolete.
Calculates the true anomaly given the time past the last periapsis passage.
Public methodToCartesian
Returns a cartesian representation of these orbital elements.
Public methodToString
Returns a string that represents the current object.
(Inherited from Object.)
Public methodStatic memberTrueAnomalyToEccentricAnomaly Obsolete.
Calculates the eccentric anomaly given the true anomaly and the eccentricity.
Public methodStatic memberTrueAnomalyToMeanAnomaly Obsolete.
Calculates the mean anomaly given the true anomaly and the eccentricity.
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Remarks
This class is meant to represent classical circular and elliptical orbits. For calculations involving parabolic or hyperbolic orbits, see ModifiedKeplerianElements.
See Also