Candidate Celestial Body Reference Frames

Creation date: 2019-02-13 20:34:25 Update date: 2019-02-14 15:41:18

Policy: Expert Review

Authority: CCSDS.MOIMS.NAV

OID: 1.3.112.4.57.2


Contents

36 records in registry

Object Identifier

Label

1.3.112.4.57.2
Celestial Body Reference Frames

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Details Status Keyword Value Name Description And Reference Nomenclature Others Have Referred To This As Frame Type References OID

Details

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).

Inertial

1.3.112.4.57.2.36

Details

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.

Inertial

1.3.112.4.57.2.35

Details

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.

Inertial

1.3.112.4.57.2.34

Details

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.

Inertial

1.3.112.4.57.2.33

Details

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.

Inertial

1.3.112.4.57.2.32

Details

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.

Inertial

1.3.112.4.57.2.31

Details

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.

Inertial

1.3.112.4.57.2.30

Details

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.

Inertial

1.3.112.4.57.2.29

Details

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.

Inertial

1.3.112.4.57.2.28

Details

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.

Inertial

1.3.112.4.57.2.27

Details

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.

Inertial

1.3.112.4.57.2.26

Details

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.

Inertial

1.3.112.4.57.2.25

Details

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].

Inertial

1.3.112.4.57.2.23

Details

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.

Inertial

1.3.112.4.57.2.21

Details

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.

Inertial

1.3.112.4.57.2.20

Details

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.

Inertial

1.3.112.4.57.2.19

Details

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

Inertial

1.3.112.4.57.2.18

Details

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.

Inertial

1.3.112.4.57.2.17

Details

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.

Inertial

1.3.112.4.57.2.16

Details

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).
Note that the term ‘J2000A coordinate system’ is not restricted to the system whose origin is at Earth’s center--- rather, the term describes a coordinate system whose origin is determined from context (i.e., for a central body, its center of mass location) whose axes are parallel to the axes of the J2000 system defined at the Earth.

Inertial

1.3.112.4.57.2.15

Details

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.
Note that the term ‘J2000 coordinate system’ is not restricted to the system whose origin is at Earth’s center--- rather, the term describes a coordinate system whose origin is determined from context (i.e., for a central body, its center of mass location) whose axes are parallel to the axes of the J2000 system defined at the Earth.

EME2000 in other CCSDS NAV Blue Books, eg ODM v2

Inertial

1.3.112.4.57.2.14

Details

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)

Inertial

1.3.112.4.57.2.12

Details

Provisional

ICRFn

The International Celestial Reference Frame is the realization of the International Celestial Reference System per IERS conventions 2003 (IERS Technical Note TN-32, ICRF1) by McCarthy and Petit and IERS 2010 conventions (TN-36, ICRF2) by Petit and Luzum. ICRF is the standard Barycentric reference system. The ICRF is periodically reevaluated, such that each realization must be annotated (i.e., ICRFn, where the ‘n’ character is an integer starting from 1). The ICRF axes are defined as the inertial (i.e., kinematically non-rotating) axes associated with a general relativity frame centered at the solar system barycenter (often called the BCRF). The IAU (International Astronomical Union) is the authority for the definition of the ICRF. The ICRF frame is realized by the transformational algorithm between it and the Earth Fixed frame.
Note that the term ‘ICRF coordinate system’ is not restricted to the system whose origin is at the solar system barycenter--- rather, the term describes a coordinate system whose origin is determined from context (i.e., for a central body, its center of mass location) whose axes are aligned with the axes of the BCRF. In fact, the IAU uses the term GCRF to refer to the system with origin at the geocenter (i.e Earth’s center of mass location) with axes parallel to the BCRF. [Note that ‘aligned’ here refers to directions in Euclidean space – not in a curved space governed by general relativity.]

e.g.,
ICRF1
ICRF2
ICRF3

Inertial

1.3.112.4.57.2.11

Details

Provisional

GCRFn

The Geocentric Celestial Reference Frame is the realization of the Geocentric Celestial Reference System per IERS conventions 2003 (IERS Technical Note TN-32, ICRF1) by McCarthy and Petit and 2010 conventions (TN-36, ICRF2) by Petit and Luzum. The underlying ICRS, from which the GCRF is derived, is periodically reevaluated. As such, each realization of the GCRF must be annotated (i.e., GCRFn, where the "n" character is an integer starting from 1). The GCRF is the standard inertial coordinate system for the Earth, with origin at the geocenter (i.e Earth’s center of mass location). The GCRF is the geocentric counterpart of the ICRF.

e.g., GCRF2

Inertial

1.3.112.4.57.2.9

Details

Provisional

EME2000

The quasi-inertial frame Earth 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.

J2000

Inertial

1.3.112.4.57.2.7