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Report Style: LOP Mean Elements

The ephemeris of the object, as observed in the object's central body's inertial coordinate system, expressed in mean orbital elements as a function of time. Mean orbital elements are calculated as used by the Long-Term Orbit Propagator (LOP). The vehicle must use the LOP propagator to produce this report.

Data Provider:LOP Mean Elements

Type: Time-varying data.

Availability: Reports | Dynamic Displays

Column Listing

Column	Column Name	Element	Type	Dimension	Description
1	Time	Time	Real Number or Text	Date	Time.
2	Semi-major Axis	Semi-major Axis	Real Number	Distance	A measure of the size of the orbit. Orbits with eccentricity <1 are ellipses, with major and minor axes identifying the symmetry axes of the ellipse, the major axis being the longer one. The value is half the length of the major axis.
3	Eccentricity	Eccentricity	Real Number	Unitless	A measure of the shape of the orbit. Values <1 indicate an ellipse (where zero is a circular orbit) and values >1 indicate a hyperbola.
4	Inclination	Inclination	Real Number or Text	Angle	The angle between the orbit plane and the XY plane of the coordinate system.
5	RAAN	RAAN	Real Number or Text	Angle	The angle in the XY plane from the X axis to the ascending node, measured in a right-handed sense about the Z axis. in the equatorial plane. For equatorial orbits, the ascending node is defined to be directed along the positive X axis, and thus the value is 0.0.
6	Arg of Perigee	Arg of Perigee	Real Number or Text	Angle	The angle from the ascending node to the periapsis vector measured in the orbit plane in the direction of the object's motion. The periapsis vector locates the closest point of the orbit. For a circular orbit, the value is defined to be zero (i.e., periapsis at the ascending node).
7	Mean Anomaly	Mean Anomaly	Real Number or Text	Angle	A measure of the time past periapsis passing, expressed as an angle.