GB/T 29077-2024 English PDF

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GB/T 29077-2024: Launch-vehicle-to-spacecraft flight environments telemetry data processing requirement
Status: Valid

GB/T 29077: Historical versions

Standard ID	USD	BUY PDF	Lead-Days	Standard Title (Description)	Status
GB/T 29077-2024	299	Add to Cart	3 days	Launch-vehicle-to-spacecraft flight environments telemetry data processing requirement	Valid
GB/T 29077-2012	150	Add to Cart	Auto, < 3 mins	Launch-vehicle-to-spacecraft flight environments telemetry data processing requirement	Obsolete

Similar standards

GB/T 43223   GB/T 32453   GB/T 29081   GB/T 29080   

Basic data

Standard ID: GB/T 29077-2024 (GB/T29077-2024)
Description (Translated English): Launch-vehicle-to-spacecraft flight environments telemetry data processing requirement
Sector / Industry: National Standard (Recommended)
Classification of Chinese Standard: V70
Word Count Estimation: 14,199
Date of Issue: 2024-05-28
Date of Implementation: 2024-09-01
Issuing agency(ies): State Administration for Market Regulation, China National Standardization Administration

GB/T 29077-2024: Launch-vehicle-to-spacecraft flight environments telemetry data processing requirement

---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.
Launch-vehicle-to-spacecraft flight environments telemetry data processing requirement Requirements for processing telemetry data of flight environment at the satellite-rocket interface Launch-vehicle-to-spacecraft flight environments telemetry data processing requirement ICS 49.020 CCS V 70 National Standards of People's Republic of China Replaces GB/T 29077-2012 Released on 2024-05-28 2024-09-01 Implementation State Administration for Market Regulation The National Standardization Administration issued

Table of Contents

Preface ... 1 Scope ... 2 Normative referenced documents ... 3 Terms and Definitions ... 4 Flight Environment Parameter Types ... 4.1 Quasi-static loads ... a) Changed the number of measurement parameters for overload, low frequency vibration, high frequency vibration, acoustic noise, shock acceleration, steady state pressure and temperature and measurement point location requirements (see 5.2.1.1, 5.2.1.2, 5.2.1.3, 5.2.1.4, 5.2.1.5, 5.2.1.6 and 5.2.1.7,.2012 Edition 5.2.1.1, 5.2.1.2, 5.2.1.3, 5.2.1.4, 5.2.1.5, 5.2.1.6 and 5.2.1.7); b) Added range selection for measurement parameters (see 5.2.2); c) Change “frequency range and minimum sampling frequency” to “sampling frequency and filtering requirements” (see 5.2.3,.2012 edition) 5.2.3); d) Added a description of the specific method for checking time history telemetry data (see 6.1.1); e) Changed the judgment basis of random signal false signal (see 6.1.3.2, 6.1.3.2 of the.2012 edition); f) Changed the data processing requirements for low-frequency vibration, high-frequency vibration, acoustic noise and impact acceleration (see 6.2.2, 6.2.3, 6.2.4 and 6.2.5, 6.2.2, 6.2.3, 6.2.4 and 6.2.5 of the.2012 edition); g) Change "delivery data format" to "output data format" (see 6.3, 6.3 of the.2012 edition); h) Deleted "delivery form" (see 6.3.1 of the.2012 edition); i) Changed the data output format for overload, low frequency vibration, high frequency vibration, acoustic noise, shock acceleration, steady state pressure, and temperature (See 6.3.1, 6.3.2, 6.3.3, 6.3.4, 6.3.5, 6.3.6 and 6.3.7,.2012 edition 6.3.2, 6.3.3, 6.3.4, 6.3.5, 6.3.6, 6.3.7 and 6.3.8); j) The chapter on flight environment results analysis report has been deleted (see Chapter 7 of the.2012 edition). k) This document was proposed and coordinated by the National Technical Committee for Standardization of Aerospace Technology and Its Applications (SAC/TC 425). This document was drafted by. Beijing Institute of Aerospace Systems Engineering, Shanghai Institute of Aerospace Systems Engineering, China Xi'an Satellite Tracking and Control Center, China Aerospace Standardization Institute. The main drafters of this document are. Jiang Renwei, Qi Feng, Zeng Yaoxiang, Yuan He, Wang Ling, Wang Mingjie, Liu Hui, Gao Yihang, Kan Lei, Wang Dan, Mao Yuming, Hu Dike, Qin Shaofei, Wang Jia, Xu Yan. This document was first published in.2012 and this is the first revision. Requirements for processing telemetry data of the flight environment at the satellite-rocket interface

1 Scope

This document specifies the types, measurement and control of the flight environment parameters of the rocket-satellite interface during the ascent phase of a launch vehicle (hereinafter referred to as the "rocket"). Parameter range and measurement requirements, data processing and methods, etc. This document is applicable to the processing and analysis of telemetry data of the satellite-rocket interface flight environment.

2 Normative references

The contents of the following documents constitute the essential clauses of this document through normative references in this document. For referenced documents without a date, only the version corresponding to that date applies to this document; for referenced documents without a date, the latest version (including all amendments) applies. in this document. GB/T 32455 Launch Vehicle Terminology

3 Terms and definitions

The terms and definitions defined in GB/T 32455 apply to this document.

4 Flight environment parameter types

4.1 Quasi-static loads Quasi-static loads are all external loads on the rocket except gravity. The frequency range is within 10 Hz and is generally represented by acceleration. 4.2 Low frequency vibration Low-frequency vibrations are mainly caused by the structural response of the rocket during ignition and shutdown caused by the engine pulsating thrust, or during transonic flight. Structural response caused by gas pressure fluctuations or transient loads during stage separation. Frequency range 2 Hz~ 100 Hz, generally represented by acceleration. 4.3 High frequency vibration High-frequency vibration is mainly caused by the structural response of the rocket engine jet noise and aerodynamic noise. The maximum value is reached in the transonic section. The frequency range is 10 Hz~2 000 Hz and is generally represented by the power spectrum density of acceleration. 4.4 Acoustic Noise Acoustic noise is mainly the sound pressure generated by rocket engine noise and aerodynamic noise. The frequency range (center frequency) is 25 Hz ~ 10 000 Hz and is generally characterized by sound pressure level. 4.5 Impact The impact environment is mainly caused by the transient response of the separation actions such as fairing separation, stage separation, and satellite-rocket separation. The frequency range is 100 Hz~10 000 Hz, generally represented by acceleration. ......

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