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 |
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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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 |
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 |
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 |
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_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 |
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 |
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_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 |
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 |
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 |
TEMEOFDATE |
For the Earth system only, specifies True Equator Mean Equinox of date quasi-inertial frame. This is an intermediate quasi-inertial frame associated with the transformation from Earth’s MeanOfDate to Earth’s TrueOfDate axes through the geometric terms of the Equation of the Equinoxes. The TEMEOfDate Z axis is aligned with the TrueOfDate Z axis; the TEMEOfDate X axis is close to (but not identical to) the MeanOfDate X axis. This is the underlying frame upon which the NORAD Two-Line Element Sets (TLEs) are based. |
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Inertial |
1.3.112.4.57.2.25 |
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Provisional |
MOON_PAxxx |
Moon Principal Axis (PA) rotating frame. This frame is aligned with the Moon’s principal inertia axes with the Z axis along the maximum inertia and the X axis along the minimum inertia. The PA frame is developed in conjunction with the development of the ephemerides for the Moon: hence, the frame depends on the source JPL DE file being used. The PAxxx frame is used as the basis for Lunar gravity models, in the numerical integration of the planetary ephemerides, and as the reference for modern moon gravity solutions. Euler angles supplied as part of the JPL DE planetary ephemerides relate the MOON_PA frame to ICRF. In this case, ‘xxx’ shall be confined to be existing JPL DE instantiations, such as PA403, PA421 and PA430 (with ‘xxx’ = 403, 421 and 430, respectively). |
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Body-Fixed |
1.3.112.4.57.2.24 |
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Provisional |
MOON_MEIAUE |
Moon-Centered, Moon Mean Equator and IAU-Node of Epoch quasi-inertial frame as specified in [Jet Propulsion Laboratory, “Lunar Constants and Models Document,” JPL D-32296, 23 Sept 2005, Fig. 6-2]. |
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Inertial |
1.3.112.4.57.2.23 |
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Provisional |
MOON_ME |
Moon Mean Earth (ME) rotating frame. This is the preferred lunar frame for associating lunar topography. It is defined as a constant rotation from the Principal Axes frame associated with a particular instantiation of the Jet Propulsion Laboratory Development Ephemeris (JPL/DE). Typically, the X axis pointed along the mean direction to the center of the Earth and the Z axis pointing to the mean direction of rotation. The ME frame is typically used to specify the location of objects on the Moon. |
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Body-Fixed |
1.3.112.4.57.2.22 |
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Provisional |
MOE_EARTH |
Mean of Epoch quasi-inertial frame definition for the Earth. The Earth’s MeanOfDate system evaluated at some specified epoch, rather than at each given time. This frame does not rotate with respect to the J2000 frame. |
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Inertial |
1.3.112.4.57.2.21 |
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Provisional |
MOE_CB |
Mean of Epoch quasi-inertial frame definition for all central bodies except Earth, where the central body shall be defined via an accompanying “CENTER_NAME”. The MeanOfDate system evaluated at some specified epoch, rather than evolving in time. This frame does not rotate with respect to the Inertial frame. |
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Inertial |
1.3.112.4.57.2.20 |
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Provisional |
MOD_MOON |
Mean of Date quasi-inertial frame definition for the Moon. The Z axis aligns with the IAU2003 Z axis, and the X axis aligns with the vector that is the cross product of the ICRF Z axis and the IAU2003 Z axis, evaluated at each given time. However, when computing the IAU2003 Z axis, the oscillatory terms are ignored. |
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Inertial |
1.3.112.4.57.2.19 |
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Provisional |
MOD_EARTH |
Mean of Date quasi-inertial frame definition for the Earth. Mean Equator and Mean Equinox of date. The transformation between J2000 and MeanOfDate is computed using a sequence of Euler rotations. Rotation angles are computed using cubic polynomials of time past the J2000 epoch in JED according to the 1976 IAU Theory of Precession angles and rates, as found in the US Naval Observatory circular No. 163. The MeanOfDate Z axis is the Earth’s mean spin axis; the MeanOfDate X axis defines the mean vernal equinox |
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Inertial |
1.3.112.4.57.2.18 |
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Provisional |
MOD_CB |
Mean 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 same computation as TOD_CB except that when the Fixed frame Z axis is computed, any oscillatory terms in the formulas for the right ascension and declination are ignored. |
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Inertial |
1.3.112.4.57.2.17 |
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Provisional |
J2000_ECLIPTIC |
The quasi-inertial frame mean ecliptic system evaluated at the J2000 epoch. The mean ecliptic plane is defined as the rotation of the J2000 XY plane about the J2000 X axis by the mean obliquity defined using FK5 IAU76 theory. |
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Inertial |
1.3.112.4.57.2.16 |
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Provisional |
J2000A |
The quasi-inertial frame Mean Equator and Mean Equinox of the J2000 epoch (JD 2451545.0 TDB which is 1 Jan 2000 12:00:00.000 TDB). The J2000 frame is the realization using the IAU 2000A by Mathews et al. (IERS TN 32 and 36). |
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Inertial |
1.3.112.4.57.2.15 |
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Provisional |
J2000 |
The quasi-inertial frame Mean Equator and Mean Equinox of the J2000 epoch (JD 2451545.0 TDB which is 1 Jan 2000 12:00:00.000 TDB). The J2000 frame is realized by the transformational algorithm (also known as the FK5 IAU76 theory) between it and the Earth Fixed frame. The algorithm uses the 1976 IAU Theory of Precession, the 1980 Nutation model, and the Greenwich Mean apparent Sidereal Time (expressed as a function of time in UT1), updated by IERS Technical Note No. 21 to include an adjustment to the equation of the equinoxes. |
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EME2000 in other CCSDS NAV Blue Books, eg ODM v2 |
Inertial |
1.3.112.4.57.2.14 |
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Provisional |
ITRFyyyy |
The rotating Earth-fixed frame that is a realization of the ITRS through estimation of ground station coordinates from observation data. The ITRF is obtained by a transformation from ICRF which includes precession, nutation, and rotation effects, as well as pole wander and frame corrections. International Terrestrial Reference Frame solution as of year “yyyy” (e.g. 1993, 1997, 2000). Realizations of the ITRS are produced by IERS under the name International Terrestrial Reference Frames (ITRF), which consist of lists of coordinates (and velocities) for a selection of IERS sites (tracking stations or related ground markers). Currently, ITRF-yyyy is published approximately annually by the IERS in the Technical Notes (cf. Boucher et al., 1996). The numbers (yyyy) following the designation "ITRF" specify the last year of data used in the formation of the frame. Hence ITRF1994 designates the frame of coordinates and velocities constructed in 1995 using all of the IERS data available through 1994. More recently, since 1993, other special realizations have been produced, such as solutions for IGS core stations (ITRF-Py series) (IGS, 1995). Note that some coordinate systems are aligned with specific ITRF solutions (e.g., GLONASS PZ-90.11 agrees with ITRF2008). |
e.g., ITRF2000 |
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Body-Fixed |
1.3.112.4.57.2.13 |
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Provisional |
INERTIAL_CB |
Inertial definition for all central bodies except the Moon, Sun and Earth, where the central body shall be defined via an accompanying “CENTER_NAME”. Each central body defines its own Inertial frame computed as a constant rotation from the ICRF frame. Inertial frames for both the Earth and Sun are defined as ICRF itself (i.e., no rotation) and an additional frame named Inertial is not defined. Due to potential vagaries in definition, the use of “Inertial_CB” is not recommended unless a more definitive frame is not available or applicable (i.e. ICRF2, J2000) |
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Inertial |
1.3.112.4.57.2.12 |
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