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 HierarchyNamespace: AGI.Foundation.Coordinates
Assembly: AGI.Foundation.Core (in AGI.Foundation.Core.dll) Version: 25.1.421.0 (25.1.421.0)
SyntaxThe KeplerianElements type exposes the following members.
Constructors| Name | Description | |
|---|---|---|
 | KeplerianElements(DelaunayElements) |
Initialize a set of classical Keplerian elements from a set of DelaunayElements.
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| KeplerianElements(EquinoctialElements) |
Initialize a set of classical Keplerian elements from a set of EquinoctialElements.
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| KeplerianElements(ModifiedKeplerianElements) |
Initialize a set of classical Keplerian elements from a set of
ModifiedKeplerianElements.
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| KeplerianElements(MotionCartesian, Double) |
Initializes a new instance from the specified Cartesian motion and gravitational parameter.
The given elements must represent a closed orbit.
For other orbit types, use ModifiedKeplerianElements.
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| KeplerianElements(Cartesian, Cartesian, Double) |
Initialize a set of classical Keplerian elements from a Cartesian position and velocity.
The given elements must represent a closed orbit.
For other orbit types, use ModifiedKeplerianElements.
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| KeplerianElements(DelaunayElements, Double, Double) |
Initialize a set of classical Keplerian elements from a set of DelaunayElements.
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| KeplerianElements(EquinoctialElements, Double, Double) |
Initialize a set of classical Keplerian elements from a set of EquinoctialElements.
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| KeplerianElements(MotionCartesian, Double, Double, Double) |
Initializes a new instance from the specified cartesian motion and gravitational constant.
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| KeplerianElements(Cartesian, Cartesian, Double, Double, Double) |
Initialize a set of classical Keplerian elements from a cartesian position and velocity.
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| KeplerianElements(Double, Double, Double, Double, Double, Double, Double) |
Initialize a set of classical Keplerian orbital elements.
The given elements must represent a closed orbit.
For other orbit types, use ModifiedKeplerianElements.
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Properties| Name | Description | |
|---|---|---|
 | ArgumentOfPeriapsis |
Gets the argument of periapsis of the orbit, in radians.
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| Eccentricity |
Gets the eccentricity of the orbit.
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| GravitationalParameter |
Gets the gravitational parameter used for this element set (distance cubed per time squared).
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| Inclination |
Gets the inclination of the orbit, in radians.
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| OrbitType |
Gets the type of orbit represented by these elements.
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| RightAscensionOfAscendingNode |
Gets the right ascension of the ascending node of the orbit, in radians.
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| SemimajorAxis |
Gets the semimajor axis of the orbit (distance).
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| TrueAnomaly |
Gets the true anomaly of the orbit, in radians.
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Methods| Name | Description | |
|---|---|---|
| Clone |
Clones this object using the specified context.
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| ComputeEccentricAnomaly |
Computes the eccentric anomaly based on the current Keplerian position.
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| ComputeMeanAnomaly |
Computes the Mean anomaly based on the current Keplerian position.
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| ComputeMeanMotion |
Computes the mean motion based on the current Keplerian elements.
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| ComputePeriod |
Computes the orbital period of the current Keplerian elements.
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| ComputeRadiusOfApoapsis |
Computes the apoapsis of the current Keplerian elements.
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| ComputeRadiusOfPeriapsis |
Computes the periapsis of the current Keplerian elements.
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| ComputeSemilatusRectum |
Computes the semilatus rectum of the current Keplerian elements.
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| 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 a cartesian representation of these orbital elements.
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| ToString | Returns a string that represents the current object. (Inherited from Object.) |
Remarks
This class is meant to represent classical circular and elliptical orbits. For
calculations involving parabolic or hyperbolic orbits, see ModifiedKeplerianElements.
See Also