Missile: Classical Elements
Classical osculating orbital elements, sometimes referred to as Keplerian elements.
The ephemeris can be requested in a variety
of coordinate systems.
The available coordinate systems depend on the object's central body.
Nominally, the systems Inertial, J2000, TrueOfDate, and MeanOfDate
are supported, although some central bodies (notably the Earth and Sun) have more.
The following lists the inertial systems available for Earth.
Type: Time-varying data
Availability: Reports | Graphs | Dynamic Displays | Strip Charts
| Name | Description |
|---|---|
| ICRF | Earth's attitude expressed with respect to the ICRF frame. |
| MeanOfDate | The mean equator mean equinox coordinate system evaluated at the requested time. |
| MeanOfEpoch | The mean equator mean equinox coordinate system evaluated at the epoch of the object. |
| TrueOfDate | The true equator true equinox coordinate system evaluated at the requested time. |
| TrueOfEpoch | The true equator true equinox coordinate system evaluated at the epoch of the object. |
| B1950 | The mean equator mean equinox coordinate system evaluated at the beginning of the Besselian year 1950 (31 December 1949 22:09:46.866 = JD 2433282.4234591). |
| TEMEOfEpoch | The true equator mean equinox coordinate system evaluated at the epoch of the object. |
| TEMEOfDate | The true equator mean equinox coordinate system evaluated at the requested time. |
| AlignmentAtEpoch | The non-rotating coordinate system coincident with the Fixed system evaluated at the object's coordinate reference epoch. |
| J2000 | The mean equator mean equinox coordinate system evaluated at the J2000.0 epoch (2000 January 1.5 = JD 2451545.0 TDB). |
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