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

CIRS

Celestial 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

1.3.112.4.57.2.4

Details

Provisional

ALIGN_CB

For all central bodies except Earth, where the central body shall be defined via an accompanying “CENTER_NAME”. An inertial frame obtained by evaluating the central body’s fixed (rotating) frame at some specified epoch, rather than evolving in time.

Inertial

1.3.112.4.57.2.1

Details

Provisional

ALIGN_EARTH

For the Earth system only, an inertial frame obtained by evaluating the Earth’s fixed (rotating) frame at some specified epoch, rather than evolving in time.

Inertial

1.3.112.4.57.2.2

Details

Provisional

B1950

For the Earth system only, these inertial axes are associated with the FK4 star catalog and its theory modeling the mean equator and mean equinox. The epoch is the beginning of the Besselian year 1950, corresponding to 31 Dec 1949 22:09:46.866 or JD 2433282.4234591. The B1950 axes are realized by a constant rotation offset from the J2000 axes, using a formula available from the Explanatory Supplement to the Astronomical Almanac.

Inertial

1.3.112.4.57.2.3

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

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

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

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

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_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

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

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

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

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.

Body-Fixed

1.3.112.4.57.2.22

Details

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).

Body-Fixed

1.3.112.4.57.2.24

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

GTOD

The Greenwich True-of-Date (GTOD) rotating coordinate system. This is realized as a rotating, right-handed, Cartesian system with the origin at the center of the Earth. The orientation of this system is specified with the xy plane in the Earth’s true of date Equator, the z axis directed along the Earth’s true of date rotational axis and is positive north, the positive x axis directed toward the prime meridian, and the y axis completing the right-handed system.

• ‘True of Date Rotating’ (TDR)
• ‘Greenwich Rotating Coordinate Frame’ (GRC)

Body-Fixed

1.3.112.4.57.2.10

Details

Provisional

FIXED_CB

The rotating fixed frame for all central bodies except Earth, where the central body shall be defined via an accompanying “CENTER_NAME”. The Fixed frame is the frame in which its topography is expressed. For gaseous planets (Jupiter, Saturn, Uranus, Neptune), the Fixed frame identifies the planet’s magnetic field instead. The Earth’s Moon realizes its Fixed frame (by default) as its Mean Earth frame; all other central bodies realize their Fixed frames using the transformational algorithm and parameters contained in Report of the IAU/IAG Working Group on cartographic coordinates and rotational elements: 2009, B.A. Archinal et al., Celest. Mech Dyn Astr 109 (2), 101-135 (DOI: 10.1007/s10569-010-9320-4).

Body-Fixed

1.3.112.4.57.2.8

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

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

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_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

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

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