GB/T 43223-2023 English PDF (GB/T43223-2023)

GB/T 43223-2023: Space objects orbital data specification
Delivery: 9 seconds. Download (and Email) true-PDF + Invoice.
Get Quotation: Click GB/T 43223-2023 (Self-service in 1-minute)
Historical versions (Master-website): GB/T 43223-2023
Preview True-PDF (Reload/Scroll-down if blank)


GB/T 43223-2023
GB
NATIONAL STANDARD OF THE
PEOPLE’S REPUBLIC OF CHINA
ICS 49.140
CCS V 70
Space objects orbital data specification
ISSUED ON: SEPTEMBER 07, 2023
IMPLEMENTED ON: JANUARY 01, 2024
Issued by: State Administration for Market Regulation;
Standardization Administration of the People’s Republic of China.
Table of Contents
Foreword ... 3
1 Scope ... 4
2 Normative references ... 4
3 Terms and definitions ... 4
4 Abbreviated terms ... 5
5 Artificial space objects orbital data specification ... 5
5.1 General ... 5
5.2 Space-time reference system ... 5
5.3 Data content and writing format ... 6
6 Near earth asteroid orbital data specification ... 10
6.1 General ... 10
6.2 Space-time reference system ... 11
6.3 Data format ... 11
Appendix A (Informative) Method for converting orbital data of space objects orbiting
the Earth into standard data recommended by CCSDS ... 13
Bibliography ... 14
Space objects orbital data specification
1 Scope
This document specifies the elements, format and description of orbital data of space
objects.
This document applies to the characterization of orbital data of artificial space objects
such as spacecraft, launch vehicles, space debris orbiting the Earth, and of natural space
objects such as near earth asteroids orbiting the Sun. The characterization of orbital data
of other spacecraft orbiting a celestial body in the solar system can also refer to this
document.
2 Normative references
The following documents are referred to in the text in such a way that some or all of
their content constitutes requirements of this document. For dated references, only the
edition cited applies. For undated references, the latest edition of the referenced
document (including any amendments) applies.
GB/T 7408, Data elements and interchange formats - Information interchange -
Representation of dates and times
GB/T 29079, Classification and parameter symbols for orbits and trajectories of
spacecraft
GB/T 32296, General coordinates for space vehicle
GB/T 34513, Space debris mitigation requirements
3 Terms and definitions
For the purpose of this document, the following terms and definitions, as well as those
given in GB/T 7408, GB/T 29079 and GB/T 34513 apply.
3.1
astronomical unit; AU
A unit of length for measuring distances within the solar system, equal to the average
distance between the Sun and the Earth, with a specific value of 149 597 870.7 km.
3.2
near earth asteroid; NEA
Asteroids orbiting the Sun in the solar system, whose perihelion is within 1.3
astronomical units of the heliocenter.
4 Abbreviated terms
For the purposes of this document, the following abbreviated terms apply.
CCSDS: Consultative Committee for Space Data Systems
GCRS: Geocentric Celestial Reference System
IAU: International Astronomical Union
ICRS: International Celestial Reference System
MPC: Minor Planet Center
OEM: Orbit Element Message
OMM: Orbit Mean-element Message
OPM: Orbit Parameter Message
UTC: Coordinated Universal Time
5 Artificial space objects orbital data specification
5.1 General
The artificial space objects orbital data is used to describe the state parameters of the
orbit of the corresponding artificial space objects around a certain central celestial body,
usually including orbital data and related dynamic parameters.
5.2 Space-time reference system
The time reference system uses UTC; the space reference system is defined according
to GB/T 32296 and is based on ICRS: the coordinate origin is the center of mass of the
central gravitational body, and the coordinate plane and coordinate axis point in the
same direction as ICRS.
Note: Taking an artificial space object orbiting the Earth as an example, the
corresponding coordinate system is GCRS. For the calculation of parameters
such as precession and nutation related to the coordinate system, it is
recommended to use the IAU1980 and newer models.
Appendix A
(Informative)
Method for converting orbital data of space objects orbiting the Earth into
standard data recommended by CCSDS
A.1 General
CCSDS provides three recommended orbital data standards: OEM, OPM, and OMM.
The conversion methods between the orbital data format specified in this document and
the OEM and OPM data formats are shown in A.2 and A.3 respectively.
A.2 Conversion with OPM
In OPM, EME2000 is used to represent the celestial coordinate system of the J2000.0
epoch. The orbital elements can be directly obtained by coordinate transformation using
the data in this document. The difference is that in OPM, atmospheric drag and solar
radiation pressure are represented by the drag coefficient/radiation pressure coefficient
and the effective area, respectively, but the effective area can be calculated by giving
the mass of the object and the drag coefficient. OPM data is usually for spacecraft that
are effectively operating on orbit, so there is a reference value for mass.
A.3 Conversion with OEM
OEM is the orbital ephemeris information. The user of this document only needs to
convert the six Kepler orbit elements into position and velocity vectors in the
corresponding coordinate system or directly use the ephemeris data. In addition, this
document provides covariance data as optional data, and its format is consistent with
OEM.
GB/T 43223-2023
GB
NATIONAL STANDARD OF THE
PEOPLE’S REPUBLIC OF CHINA
ICS 49.140
CCS V 70
Space objects orbital data specification
ISSUED ON: SEPTEMBER 07, 2023
IMPLEMENTED ON: JANUARY 01, 2024
Issued by: State Administration for Market Regulation;
Standardization Administration of the People’s Republic of China.
Table of Contents
Foreword ... 3
1 Scope ... 4
2 Normative references ... 4
3 Terms and definitions ... 4
4 Abbreviated terms ... 5
5 Artificial space objects orbital data specification ... 5
5.1 General ... 5
5.2 Space-time reference system ... 5
5.3 Data content and writing format ... 6
6 Near earth asteroid orbital data specification ... 10
6.1 General ... 10
6.2 Space-time reference system ... 11
6.3 Data format ... 11
Appendix A (Informative) Method for converting orbital data of space objects orbiting
the Earth into standard data recommended by CCSDS ... 13
Bibliography ... 14
Space objects orbital data specification
1 Scope
This document specifies the elements, format and description of orbital data of space
objects.
This document applies to the characterization of orbital data of artificial space objects
such as spacecraft, launch vehicles, space debris orbiting the Earth, and of natural space
objects such as near earth asteroids orbiting the Sun. The characterization of orbital data
of other spacecraft orbiting a celestial body in the solar system can also refer to this
document.
2 Normative references
The following documents are referred to in the text in such a way that some or all of
their content constitutes requirements of this document. For dated references, only the
edition cited applies. For undated references, the latest edition of the referenced
document (including any amendments) applies.
GB/T 7408, Data elements and interchange formats - Information interchange -
Representation of dates and times
GB/T 29079, Classification and parameter symbols for orbits and trajectories of
spacecraft
GB/T 32296, General coordinates for space vehicle
GB/T 34513, Space debris mitigation requirements
3 Terms and definitions
For the purpose of this document, the following terms and definitions, as well as those
given in GB/T 7408, GB/T 29079 and GB/T 34513 apply.
3.1
astronomical unit; AU
A unit of length for measuring distances within the solar system, equal to the average
distance between the Sun and the Earth, with a specific value of 149 597 870.7 km.
3.2
near earth asteroid; NEA
Asteroids orbiting the Sun in the solar system, whose perihelion is within 1.3
astronomical units of the heliocenter.
4 Abbreviated terms
For the purposes of this document, the following abbreviated terms apply.
CCSDS: Consultative Committee for Space Data Systems
GCRS: Geocentric Celestial Reference System
IAU: International Astronomical Union
ICRS: International Celestial Reference System
MPC: Minor Planet Center
OEM: Orbit Element Message
OMM: Orbit Mean-element Message
OPM: Orbit Parameter Message
UTC: Coordinated Universal Time
5 Artificial space objects orbital data specification
5.1 General
The artificial space objects orbital data is used to describe the state parameters of the
orbit of the corresponding artificial space objects around a certain central celestial body,
usually including orbital data and related dynamic parameters.
5.2 Space-time reference system
The time reference system uses UTC; the space reference system is defined according
to GB/T 32296 and is based on ICRS: the coordinate origin is the center of mass of the
central gravitational body, and the coordinate plane and coordinate axis point in the
same direction as ICRS.
Note: Taking an artificial space object orbiting the Earth as an example, the
corresponding coordinate system is GCRS. For the calculation of parameters
such as precession and nutation related to the coordinate system, it is
recommended to use the IAU1980 and newer models.
Appendix A
(Informative)
Method for converting orbital data of space objects orbiting the Earth into
standard data recommended by CCSDS
A.1 General
CCSDS provides three recommended orbital data standards: OEM, OPM, and OMM.
The conversion methods between the orbital data format specified in this document and
the OEM and OPM data formats are shown in A.2 and A.3 respectively.
A.2 Conversion with OPM
In OPM, EME2000 is used to represent the celestial coordinate system of the J2000.0
epoch. The orbital elements can be directly obtained by coordinate transformation using
the data in this document. The difference is that in OPM, atmospheric drag and solar
radiation pressure are represented by the drag coefficient/radiation pressure coefficient
and the effective area, respectively, but the effective area can be calculated by giving
the mass of the object and the drag coefficient. OPM data is usually for spacecraft that
are effectively operating on orbit, so there is a reference value for mass.
A.3 Conversion with OEM
OEM is the orbital ephemeris information. The user of this document only needs to
convert the six Kepler orbit elements into position and velocity vectors in the
corresponding coordinate system or directly use the ephemeris data. In addition, this
document provides covariance data as optional data, and its format is consistent with
OEM.