Name

Description

AGOM

The AGOM (area * gamma / mass ) term used in the SDP4 and SGP4XP propagation model. Note that this term aliases Cr in the same way that B* aliases Cd.

Alpha5ID

The Alpha5 catalog id assigned to the object by the US Space Force. This maps to the SatelliteNumber using the alpha encoding defined by the US Space Force.

Bstar

A special "drag" term associated with the SGP4 propagator. It measured in units of 1/earth radii and is related to the Spacecraft's Cd. It is obtained by having FreeFlyer import a TwoLine Element (TLE) state vector. It is also computed by FreeFlyer when a conversion from Cartesian elements to SGP4 elements is invoked.

DeclaredName

The name of the object as declared.

DisplayName

The name displayed for this object in output windows such as views, plots, and reports.

E

The SGP4 element set Eccentricity.

EphemerisType

The ephemeris type of the SGP4 state elements. Type 0 indicates the state elements are calculated and should be propagated using the SGP4 algorithm, and present mean motion as the Kozai mean motion. Type 2 indicates the state elements are calculated and should be propagated using the SGP4/SDP4 algorithm, and present mean motion as the Brouwer mean motion. Type 4 indicates that the state elements are calculated and should be propagated using the SGP4XP algorithm.

EquinoctialH

The h component of the SGP4 based Equinoctial element set, defined by: h = e*sin(RAAN + w), where e, w, and RAAN are the SGP4 Eccentricity, Argument of Perigee and Right Ascension of the Ascending Node respectively. These orbit properties are with respect to the True Equator Mean Equinox coordinate frame.

EquinoctialK

The k component of the SGP4 based Equinoctial element set, defined by: k = e*cos(RAAN + w), where e, w, and RAAN are the SGP4 Eccentricity, Argument of Perigee and Right Ascension of the Ascending Node respectively. These orbit properties are with respect to the True Equator Mean Equinox coordinate frame.

EquinoctialLongitude

Equinoctial SGP4 based Longitude defined by the mean longitude, defined as: RAAN + w + MA, where RAAN and w are the Right Ascension of the Ascending Node and the Argument of Perigee, respectively, and MA is the Keplerian mean anomaly. These orbit properties are with respect to the True Equator Mean Equinox coordinate frame.

EquinoctialMeanMotion

The SGP4 element set Mean Motion, referenced to the True Equator Mean Equinox coordinate frame.

EquinoctialP

The p component of the SGP4 based Equinoctial element set, defined by: p = tan(i/2)sin(RAAN), where i is the orbit inclination and RAAN is the SGP4 Right Ascension of the Ascending Node. These orbit properties are with respect to the True Equator Mean Equinox coordinate frame.

EquinoctialQ

The q component of the SGP4 based Equinoctial element set, defined by: q = tan(i/2)cos(RAAN) where i is the orbit inclination and RAAN is the SGP4 Right Ascension of the Ascending Node. These orbit properties are with respect to the True Equator Mean Equinox coordinate frame.

I

The SGP4 element set Inclination, referenced to the True Equator Mean Equinox coordinate frame.

MA

The SGP4 element set Mean Anomaly, referenced to the True Equator Mean Equinox coordinate frame.

MeanMotion

The SGP4 element set Mean Motion, referenced to the True Equator Mean Equinox coordinate frame.

ObjectId

The unique identifier for the object.

ObjectType

The type of the object.

RAAN

The SGP4 element set Right Ascension of the Ascending Node, referenced to the True Equator Mean Equinox coordinate frame.

SatelliteNumber

The catalog number assigned to the object by the US Space Force. This maps to the Alpha5ID using the alpha encoding defined by the US Space Force.

W

The SGP4 element set Argument of Perigee, referenced to the True Equator Mean Equinox coordinate frame.
