Candidate Celestial Body Reference Frames
Policy: Expert Review
Authority: CCSDS.MOIMS.NAV
OID: 1.3.112.4.57.2
Contents
36 records in registry
Object Identifier
Label
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Details | Status | Keyword Value Name | Description And Reference | Nomenclature | Others Have Referred To This As | Frame Type | References | OID | |
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Provisional |
TEMEOFEPOCH |
For the Earth system only, specifies the quasi-inertial True Equator Mean Equinox of epoch frame. Earth’s TEMEOfDate frame evaluated at some specified epoch rather than evolving in time. The frame does not rotate with respect to the J2000 frame. |
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Inertial |
1.3.112.4.57.2.26 |
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Provisional |
TIRS |
Terrestrial Intermediate Reference System. Details in IERS TN32 5.11 and TN36 p. 47 and Vallado [Vallado, D., Seago, J., Seidelmann, P. (2006). Implementation Issues Surrounding the New IAU Reference Systems for Astrodynamics. 16th AAS/AIAA Space Flight Mechanics Conference]. Essentially the transformation for precession/nutation is based on the Celestial Intermediate Pole realized with the IAU2000A model rather than IAU1976/80. |
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Inertial |
1.3.112.4.57.2.27 |
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Provisional |
TOD_CB |
True of Date quasi-inertial frame definition for all central bodies except Earth and Moon, where the central body shall be defined via an accompanying “CENTER_NAME”. The Z axis aligns with the central body’s Fixed Z axis, and the X axis aligns with the vector that is the cross product of the ICRF Z axis and the Fixed Z axis, evaluated at each given time. If the cross product is zero, then the Y axis aligns with the cross product of the Fixed Z axis and the ICRF X axis. |
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Inertial |
1.3.112.4.57.2.28 |
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Provisional |
TOD_EARTH |
True of Date quasi-inertial frame definition for the Earth. True Equator and True Equinox of date. The transformation between Earth’s MeanOfDate to Earth’s TrueOfDate axes uses the mean obliquity, the nutation in longitude, and the nutation in obliquity, computed according to the 1980 Nutation model, and then applies the update to the equation of the equinoxes. By default, the nutation values are obtained by interpolating values contained in the JPL DE file rather than evaluating the model directly. The TrueOfDate Z axis would be the Earth’s spin axis if pole wander were ignored; the TrueOfDate X axis defines the true vernal equinox. |
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Inertial |
1.3.112.4.57.2.29 |
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Provisional |
TOD_MOON |
True of Date quasi-inertial frame definition for the Moon. The Z axis aligns with the Fixed Z axis, and the X axis aligns with the vector that is the cross product of the ICRF Z axis and the Fixed Z axis, evaluated at each given time. The TrueOfDate frame is very close to the Mean Lunar Equator and IAU Node of Date (Lunar Constants and Model Document, JPL D-32296, Sept 2005). If the Moon’s Fixed frame were to be set to use the IAU2003 frame, then the two frames would be identical. |
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Inertial |
1.3.112.4.57.2.30 |
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Provisional |
TOE_CB |
True of Epoch definition for all central bodies except Earth and Moon, where the central body shall be defined via an accompanying “CENTER_NAME”. The central body’s TrueOfDate system (TOD_CB) evaluated at some specified epoch, rather than evolving over time. This frame does not rotate with respect to the ICRF frame. |
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Inertial |
1.3.112.4.57.2.31 |
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Provisional |
TOE_EARTH |
True of Epoch definition for the Earth. The Earth’s TrueOfDate system (TOD_EARTH) evaluated at some specified epoch, rather than evolving over time. This frame does not rotate with respect to the ICRF frame. |
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Inertial |
1.3.112.4.57.2.32 |
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Provisional |
TOE_MOON |
True of Epoch definition for the Moon. The Moon’s TrueOfDate system (TOD_MOON) evaluated at some specified epoch, rather than evolving over time. This frame does not rotate with respect to the ICRF frame. |
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Inertial |
1.3.112.4.57.2.33 |
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Provisional |
TRUE_ECLIPTIC |
The true ecliptic system, evolving in time. The true ecliptic plane is defined as the rotation of the J2000 XY plane about the J2000 X axis by the true obliquity defined using FK5 IAU76 theory. |
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Inertial |
1.3.112.4.57.2.34 |
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Provisional |
UVW_GO_INERTIAL |
Launch go-inertial reference frame, with U in local horizon plane along inertial launch azimuth (downrange), W along the geodetic vertical and V completing the set (cross-range). In typical use the go-inertial epoch should be specified in an accompanying comment field. |
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Inertial |
1.3.112.4.57.2.35 |
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Provisional |
WGS84 |
WGS 84 is an Earth-centered, Earth-fixed terrestrial reference system and geodetic datum. WGS 84 is based on a consistent set of constants and model parameters that describe the Earth's size, shape, and gravity and geomagnetic fields. WGS 84 is the standard U.S. Department of Defense definition of a global reference system for geospatial information and is the reference system for the Global Positioning System (GPS). It is compatible with the International Terrestrial Reference System (ITRS). |
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Inertial |
1.3.112.4.57.2.36 |
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