Keplerian Elements components are a subset of Calculation Object components. They are the classical elements specifying an orbit by itz size, shape and three-dimensional orientation in space.
ComponentBrowser */ SetValue "Calculation Objects" {Component} {Attribute} <Value> [{Unit}]
ComponentBrowser */ Duplicate "Calculation Objects" {Component} <Duplicate Component Name>
The Keplerian Elements components are:
| Component | Description |
|---|---|
| Altitude of Apoapsis | Altitude at apoapsis of the conic orbit |
| Altitude of Periapsis | Altitude at periapsis of the conic orbit |
| Argument of Latitude | Sum of argument of periapsis and true anomaly |
| Argument of Periapsis | Angular distance from the ascending node to periapsis |
| Eccentric Anomaly | Eccentric Anomaly of conic orbit |
| Eccentricity | Eccentricity of the conic orbit |
| Inclination | Inclination of the plane of the orbit |
| Longitude of Ascending Node | Longitude of Ascending Node |
| MeanAnomaly | Mean anomaly of the orbiting object |
| Mean Motion | Mean Motion (revs/sec) of conic orbit |
| Orbit Period | Period of the conic orbit |
| RAAN | Right Ascension of the Ascending Node of the plane of the orbit |
| Radius of Apoapsis | Radius at apoapsis of the conic orbit |
| Radius of Periapsis | Radius at periapsis of the conic orbit |
| Semimajor Axis | Half the major axis of the conic orbit |
| Time Past Asc Node | Time past the ascending node of the conic orbit |
| Time Past Periapsis | Time past the periapsis of the conic orbit |
| True Anomaly | Angular distance between the orbiting object and periapsis |
The attributes for each component have the same names and value selections that appear in the Astrogator graphical user interface.
ComponentBrowser */ Duplicate "Calculation Objects" RAAN "My RAAN"
ComponentBrowser */ SetValue "Calculation Objects" "My Inclination" CoordSystem "CentralBody/Earth J2000"
STK Programming Interface 11.0.1