Codeofchina.com is in charge of this English translation. In case of any doubt about the English translation, the Chinese original shall be considered authoritative.
Annex A to this standard is informative.
This standard was proposed by the Electronic Information Base Department of the General Armaments Department of the PLA.
Pedigree for satellite fairing
1 Scope
This standard specifies the selection and application principles of satellite fairing (hereinafter referred to as fairing).
This standard is applicable to the design of fairing and the selection of fairing by satellite, and may be used as a reference for the selection of fairing by other payloads.
2 Normative references
The following normative documents contain provisions which, through reference in this text, constitute provisions of this standard. For dated references, subsequent amendments (excluding corrections) to, or revisions, of any of these publications do not apply. However parties to agreements based on this standard are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references or references with version not indicated, the latest edition of the normative document referred to applies.
GJB 4228 Series for mechanical interface for spacecraft to launch vehicle
3 Terms
For the purpose of this standard, the following terms and definitions apply.
3.1
payload
satellite installed in a fairing and launched by a launch vehicle
3.2
fairing
launch vehicle structure which provides good environmental conditions and installation space for the satellite, protects the satellite from aerodynamic force and aerodynamic heat during the flight of the launch vehicle, and is thrown away after the launch vehicle flies out of the atmosphere
3.3
diameter of the fairing
nominal outside diameter of cylindrical section of satellite fairing
3.4
static envelop of the fairing
maximum static space that a satellite can use in a fairing
3.5
envelop diameter of the fairing
diameter of maximum cylindrical section in static envelope of fairing
4 Elements of pedigree for fairing
The pedigree for fairing mainly consists of the following elements:
a) diameter of cylindrical section of the fairing;
b) length of cylindrical section of the fairing;
c) separation mode of the fairing;
d) envelope diameter of the fairing.
5 Pedigree for fairing
See Table 1 for the requirements of pedigree for fairing.
6 Application principles of pedigree for fairing
The application principles of pedigree for fairing are as follows:
a) the series dimensions of fairing for newly developed launch vehicle shall be selected according to Table 1;
b) for newly developed launch vehicle, the maximum outside dimension of the satellite shall be designed as static envelope dimension of the fairing as specified in Table 1, and the series specified in GJB 4228 shall be selected for mechanical interface between the satellite and the launch vehicle;
c) the diameter series and static envelope of satellite fairing which are used but not listed in Table 1 shall not be used in the new satellite design.
Foreword i 1 Scope 2 Normative references 3 Terms 4 Elements of pedigree for fairing 5 Pedigree for fairing 6 Application principles of pedigree for fairing Annex A (Informative) Static envelope diagram of launch vehicle fairing
Codeofchina.com is in charge of this English translation. In case of any doubt about the English translation, the Chinese original shall be considered authoritative.
Annex A to this standard is informative.
This standard was proposed by the Electronic Information Base Department of the General Armaments Department of the PLA.
Pedigree for satellite fairing
1 Scope
This standard specifies the selection and application principles of satellite fairing (hereinafter referred to as fairing).
This standard is applicable to the design of fairing and the selection of fairing by satellite, and may be used as a reference for the selection of fairing by other payloads.
2 Normative references
The following normative documents contain provisions which, through reference in this text, constitute provisions of this standard. For dated references, subsequent amendments (excluding corrections) to, or revisions, of any of these publications do not apply. However parties to agreements based on this standard are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references or references with version not indicated, the latest edition of the normative document referred to applies.
GJB 4228 Series for mechanical interface for spacecraft to launch vehicle
3 Terms
For the purpose of this standard, the following terms and definitions apply.
3.1
payload
satellite installed in a fairing and launched by a launch vehicle
3.2
fairing
launch vehicle structure which provides good environmental conditions and installation space for the satellite, protects the satellite from aerodynamic force and aerodynamic heat during the flight of the launch vehicle, and is thrown away after the launch vehicle flies out of the atmosphere
3.3
diameter of the fairing
nominal outside diameter of cylindrical section of satellite fairing
3.4
static envelop of the fairing
maximum static space that a satellite can use in a fairing
3.5
envelop diameter of the fairing
diameter of maximum cylindrical section in static envelope of fairing
4 Elements of pedigree for fairing
The pedigree for fairing mainly consists of the following elements:
a) diameter of cylindrical section of the fairing;
b) length of cylindrical section of the fairing;
c) separation mode of the fairing;
d) envelope diameter of the fairing.
5 Pedigree for fairing
See Table 1 for the requirements of pedigree for fairing.
6 Application principles of pedigree for fairing
The application principles of pedigree for fairing are as follows:
a) the series dimensions of fairing for newly developed launch vehicle shall be selected according to Table 1;
b) for newly developed launch vehicle, the maximum outside dimension of the satellite shall be designed as static envelope dimension of the fairing as specified in Table 1, and the series specified in GJB 4228 shall be selected for mechanical interface between the satellite and the launch vehicle;
c) the diameter series and static envelope of satellite fairing which are used but not listed in Table 1 shall not be used in the new satellite design.
Contents of GJB 7238-2011
Foreword i
1 Scope
2 Normative references
3 Terms
4 Elements of pedigree for fairing
5 Pedigree for fairing
6 Application principles of pedigree for fairing
Annex A (Informative) Static envelope diagram of launch vehicle fairing
