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: 24.3.420.0 (24.3.420.0)
SyntaxThe KeplerianElements type exposes the following members.
Constructors| Name | Description | |
|---|---|---|
 | KeplerianElements(DelaunayElements) |
Initialize a set of classical Keplerian elements from a set of DelaunayElements.
|
| KeplerianElements(EquinoctialElements) |
Initialize a set of classical Keplerian elements from a set of EquinoctialElements.
|
| KeplerianElements(ModifiedKeplerianElements) |
Initialize a set of classical Keplerian elements from a set of
ModifiedKeplerianElements.
|
| 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.
|
| 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.
|
| KeplerianElements(DelaunayElements, Double, Double) |
Initialize a set of classical Keplerian elements from a set of DelaunayElements.
|
| KeplerianElements(EquinoctialElements, Double, Double) |
Initialize a set of classical Keplerian elements from a set of EquinoctialElements.
|
| KeplerianElements(MotionCartesian, Double, Double, Double) |
Initializes a new instance from the specified cartesian motion and gravitational constant.
|
| KeplerianElements(Cartesian, Cartesian, Double, Double, Double) |
Initialize a set of classical Keplerian elements from a cartesian position and velocity.
|
| 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.
|
Properties| Name | Description | |
|---|---|---|
 | ArgumentOfPeriapsis |
Gets the argument of periapsis of the orbit, in radians.
|
| Eccentricity |
Gets the eccentricity of the orbit.
|
| GravitationalParameter |
Gets the gravitational parameter used for this element set (distance cubed per time squared).
|
| Inclination |
Gets the inclination of the orbit, in radians.
|
| OrbitType |
Gets the type of orbit represented by these elements.
|
| RightAscensionOfAscendingNode |
Gets the right ascension of the ascending node of the orbit, in radians.
|
| SemimajorAxis |
Gets the semimajor axis of the orbit (distance).
|
| TrueAnomaly |
Gets the true anomaly of the orbit, in radians.
|
Methods| Name | Description | |
|---|---|---|
| Clone |
Clones this object using the specified context.
|
| ComputeEccentricAnomaly |
Computes the eccentric anomaly based on the current Keplerian position.
|
| ComputeMeanAnomaly |
Computes the Mean anomaly based on the current Keplerian position.
|
| ComputeMeanMotion |
Computes the mean motion based on the current Keplerian elements.
|
| ComputePeriod |
Computes the orbital period of the current Keplerian elements.
|
| ComputeRadiusOfApoapsis |
Computes the apoapsis of the current Keplerian elements.
|
| ComputeRadiusOfPeriapsis |
Computes the periapsis of the current Keplerian elements.
|
| ComputeSemilatusRectum |
Computes the semilatus rectum of the current Keplerian elements.
|
| 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.
|
| 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