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GB/T 32300-2015: Best practices for orbit elements at payload-launch vehicle separation
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| Standard ID | Contents [version] | USD | STEP2 | [PDF] delivered in | Standard Title (Description) | Status | PDF |
| GB/T 32300-2015 | English | 319 |
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Best practices for orbit elements at payload-launch vehicle separation
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GB/T 32300-2015
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Basic data | Standard ID | GB/T 32300-2015 (GB/T32300-2015) | | Description (Translated English) | Best practices for orbit elements at payload-launch vehicle separation | | Sector / Industry | National Standard (Recommended) | | Classification of Chinese Standard | V73 | | Classification of International Standard | 49.020 | | Word Count Estimation | 15,184 | | Date of Issue | 2015-12-31 | | Date of Implementation | 2016-07-01 | | Quoted Standard | ANSI/AIAA S-131-2010; CCSDS 500.0-G-3 | | Regulation (derived from) | State Standard Announcement 2015 No.43 | | Issuing agency(ies) | General Administration of Quality Supervision, Inspection and Quarantine of the People's Republic of China, Standardization Administration of the People's Republic of China | | Summary | This standard specifies the calculation method of the bearer elements of the launch vehicle and the payload separation point, including the orbital elements and calculation conditions, the computation method of the holding elements, and the calculating method of the essential factors of the obstruction. This standard applies to calculation methods of orbit elements of different payloads such as satellites, manned spacecrafts and space stations. It is applicable to different orbits such as low earth orbit, solar synchronous orbit, medium earth orbit, geosynchronous transfer orbit and geosynchronous orbit. | GB/T 32300-2015: Best practices for orbit elements at payload-launch vehicle separation---This is a DRAFT version for illustration, not a final translation. Full copy of true-PDF in English version (including equations, symbols, images, flow-chart, tables, and figures etc.) will be manually/carefully translated upon your order.
Best practices for orbit elements at payload-launch vehicle separation
ICS 49.020
V73
National Standards of People's Republic of China
Carrier rockets and payload separation points
Calculate best practices
2015-12-31 released
2016-07-01 implementation
General Administration of Quality Supervision, Inspection and Quarantine of the People's Republic of China
China National Standardization Management Committee released
Foreword
This standard is drafted in accordance with the rules given in GB/T 1.1-2009.
This standard is proposed by China Aerospace Science and Technology Corporation.
This standard is nationalized by the National Aeronautical Technology and Its Application Standardization Technical Committee (SAC/TC425).
The drafting of this standard. Beijing Aerospace Automation Research Institute.
The main drafters of this standard. Yu Chunmei, Liu Jiarun, Lvxin Guang, Xu Guoqiang, Cao Jie, Xu Fan, Gong Qinghai.
Introduction
There are a variety of sets of track elements, suitable for different applications, this standard describes the star arrow separation time corresponding to the Kepler orbit
The internal and external measurement data sources, the relevant coordinate system and the time system of the orbital elements of the separation time are defined; the Keplerian orbit elements are provided
Of the star arrow separation point calculation method, as well as Kepler track elements into other elements of the method; proposed as a measure of launch vehicle launch
Whether the task is successfully completed by the important basis of the orbital element error calculation method.
Carrier rockets and payload separation points
Calculate best practices
1 Scope
This standard specifies the method of calculating the orbital elements of the launch vehicle and the payload separation point, including the track elements and the calculation conditions, the track elements
Calculation method, calculation method of orbital element error.
This standard applies to satellites, manned spacecraft, space stations and other different payload elements of the calculation method for low Earth orbit,
Solar synchronous orbit, middle earth orbit, geosynchronous transfer orbit, geosynchronous orbit and other different orbits.
2 normative reference documents
The following documents are indispensable for the application of this document. For dated references, only the dated edition applies to this article
Pieces. For undated references, the latest edition (including all modifications) applies to this document.
ANSI/AIAAS-131-2010 Astromodel Dynamics Definitions and Recommended Practices (Astrodynamics-Propagation
specifications, technicaldefinitions, andrecommendedpractices)
CCSDS500.0-G-3 Spatial Data System Navigation Data Definition (Reportconcerningspacedatasystemstand-
ards-navigationdatadefinitionsandconventions
3 symbols and abbreviations
3.1 symbols
The symbols in Table 1 apply to this document.
Table 1 symbols
Symbol name unit
A remote location m (m)
a semi-long axis (m)
ae equatorial radius m (m)
b semi-short axis (m)
C Geometry Center -
E Approximate angle radian (rad)
e eccentricity -
GM Earth Gravitational Constant Cubic Per Second Square Seconds (m3/s2)
ha Height of distance (m)
hp perigee height m (m)
i orbital inclination radian (rad)
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