EN 16603-50-02-2014 en Space engineering - Ranging and Doppler tracking《航天工程 移动及多普勒跟踪》.pdf

1、BSI Standards PublicationBS EN 16603-50-02:2014Space engineering Rangingand Doppler trackingBS EN 16603-50-02:2014 BRITISH STANDARDNational forewordThis British Standard is the UK implementation of EN16603-50-02:2014.The UK participation in its preparation was entrusted to TechnicalCommittee ACE/68,

2、 Space systems and operations.A list of organizations represented on this committee can beobtained on request to its secretary.This publication does not purport to include all the necessaryprovisions of a contract. Users are responsible for its correctapplication. The British Standards Institution 2

3、014. Published by BSI StandardsLimited 2014ISBN 978 0 580 84099 9ICS 49.140Compliance with a British Standard cannot confer immunity fromlegal obligations.This British Standard was published under the authority of theStandards Policy and Strategy Committee on 30 September 2014.Amendments issued sinc

4、e publicationDate Text affectedBS EN 16603-50-02:2014EUROPEAN STANDARD NORME EUROPENNE EUROPISCHE NORM EN 16603-50-02 September 2014 ICS 49.140 English version Space engineering - Ranging and Doppler tracking Ingnierie spatiale - Mesure de distance et suivi Doppler Raumfahrttechnik - Entfernungsbest

5、immung und Dopplerverfolgung This European Standard was approved by CEN on 1 March 2014. CEN and CENELEC members are bound to comply with the CEN/CENELEC Internal Regulations which stipulate the conditions for giving this European Standard the status of a national standard without any alteration. Up

6、-to-date lists and bibliographical references concerning such national standards may be obtained on application to the CEN-CENELEC Management Centre or to any CEN and CENELEC member. This European Standard exists in three official versions (English, French, German). A version in any other language m

7、ade by translation under the responsibility of a CEN and CENELEC member into its own language and notified to the CEN-CENELEC Management Centre has the same status as the official versions. CEN and CENELEC members are the national standards bodies and national electrotechnical committees of Austria,

8、 Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugoslav Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, S

9、witzerland, Turkey and United Kingdom. CEN-CENELEC Management Centre: Avenue Marnix 17, B-1000 Brussels 2014 CEN/CENELEC All rights of exploitation in any form and by any means reserved worldwide for CEN national Members and for CENELEC Members. Ref. No. EN 16603-50-02:2014 EBS EN 16603-50-02:2014EN

10、 16603-50-02:2014 (E) 2 Table of contents Foreword 4 Introduction 5 1 Scope . 6 2 Normative references . 7 3 Terms, definitions and abbreviated terms 8 3.1 Terms from other standards 8 3.2 Terms specific to the present standard . 8 3.3 Abbreviated terms. 8 4 Requirements 10 4.1 Functional . 10 4.1.1

11、 Functional breakdown . 10 4.1.2 Earth-to-Space link function 12 4.1.3 Transponder function 12 4.1.4 Space-to-Earth link function 13 4.1.5 Link control function 14 4.1.6 Data acquisition function . 14 4.2 Frequency assignment, modulation and spectral sharing 15 4.2.1 Frequency assignment 15 4.2.2 Mo

12、dulation 16 4.2.3 Spectral sharing 18 4.3 Carrier frequency stability . 22 4.4 Earth station . 24 4.4.1 Earth-to-Space link 24 4.4.2 Space-to-Earth link 25 4.5 Spacecraft transponder 27 4.5.1 General . 27 4.5.2 Range and range rate operations 27 4.5.3 Range only operations 28 4.5.4 Group delay 28 BS

13、 EN 16603-50-02:2014EN 16603-50-02:2014 (E) 3 4.5.5 Telemetered monitoring 29 4.5.6 Amplitude response 29 4.5.7 Phase modulation . 30 4.5.8 Baseband automatic gain control (AGC) . 30 4.5.9 Modulation index . 30 4.5.10 Ranging technological loss 30 4.6 Performance . 31 4.6.1 Overview . 31 4.6.2 Integ

14、rated Doppler performance 31 4.6.3 Ranging performance 32 4.6.4 Ancillary measurements 33 5 Compatibility testing 35 5.1 General . 35 5.2 Tests. 35 Annex A (informative) Compatibility with other ground stations networks . 37 Annex B (informative) Transponder ranging technological loss 39 Annex C (in

15、formative) Integrated Doppler measurement 40 Bibliography . 42 Figures Figure 4-1: Ranging and Doppler tracking: functional block diagram 11 Figure 4-2: Ranging signal spectrum for code length = 2018 Figure 4-3: Ranging signal spectrum for code length = 2219 Figure 4-4: Ranging signal spectrum for c

16、ode length = 2419 Figure 4-5: Ranging signal spectrum for code length = 212. 20 Figure 4-6: Carrier frequency stability requirements . 23 Figure C-1 :Integrated Doppler measurement 41 BS EN 16603-50-02:2014EN 16603-50-02:2014 (E) 4 Foreword This document (EN 16603-50-02:2014) has been prepared by Te

17、chnical Committee CEN/CLC/TC 5 “Space”, the secretariat of which is held by DIN. This standard (EN 16603-50-02:2014) originates from ECSS-E-ST-50-02C. This European Standard shall be given the status of a national standard, either by publication of an identical text or by endorsement, at the latest

18、by March 2015, and conflicting national standards shall be withdrawn at the latest by March 2015. Attention is drawn to the possibility that some of the elements of this document may be the subject of patent rights. CEN and/or CENELEC shall not be held responsible for identifying any or all such pat

19、ent rights. This document has been prepared under a mandate given to CEN by the European Commission and the European Free Trade Association. This document has been developed to cover specifically space systems and has therefore precedence over any EN covering the same scope but with a wider domain o

20、f applicability (e.g. : aerospace). According to the CEN-CENELEC Internal Regulations, the national standards organizations of the following countries are bound to implement this European Standard: Austria, Belgium, Bulgaria, Croatia, Cyprus, Czech Republic, Denmark, Estonia, Finland, Former Yugosla

21、v Republic of Macedonia, France, Germany, Greece, Hungary, Iceland, Ireland, Italy, Latvia, Lithuania, Luxembourg, Malta, Netherlands, Norway, Poland, Portugal, Romania, Slovakia, Slovenia, Spain, Sweden, Switzerland, Turkey and the United Kingdom. BS EN 16603-50-02:2014EN 16603-50-02:2014 (E) 5 Int

22、roduction The purpose of this Standard is to: Ensure compatibility between space agencies spacecraft transponders and the ranging and Doppler tracking facilities of the Earth stations for the Space Operation, Space Research and Earth Exploration Satellite services. Ensure, as far as possible, compat

23、ibility between space agencies spacecraft transponders and other networks from which they request support. Ensure an adequate level of ranging and Doppler tracking accuracy for missions conforming to this standard. Facilitate the early design of flight hardware and ensure that the resulting interfac

24、es and system performances are compatible with given ranging and Doppler tracking configurations and specifications. BS EN 16603-50-02:2014EN 16603-50-02:2014 (E) 6 1 Scope This Standard is applicable to spacecraft that are supported for ranging or Dop-pler tracking by direct links to Earth stations

25、 and to all related Earth stations (therefore, this Standard is not applicable for spacecraft supported by data relay satellites) operating within the Space Operation, Space Research and Earth Exploration Satellite services (therefore, this Standard is not applicable to the Meteorological Satellite

26、service) as defined in ECSS-E-ST-50-05 clause 1. Other space telecommunication services are not covered in this issue. This Standard applies to projects with unprocessed ranging accuracies of 2,5ns to 30 ns (for conventional projects with tracking accuracies less stringent than these, CCSDS 401.0-B

27、recommendations may be sufficient) and Doppler tracking accuracies of 0,1 mm/s to 1 mm/s. The analysis of compatibility between systems compliant with this standard and with the CCSDS recommendations is given in Annexes A.2 and A.3. This document: Defines the requirements concerning spacecraft trans

28、ponder and Earth station equipment for the purposes of ranging and Doppler tracking. Provides criteria by which the extent to which the accuracy of the measurements is influenced by equipment effects can be determined. This accuracy is different to the accuracy of the overall orbit determination pro

29、cess, which is also influenced by effects outside the scope of the standards, i.e. modelling of gravitational and non-gravitational forces, modelling of propagation effects, pre-processing and screening of data. This standard may be tailored for the specific characteristics and constraints of a spac

30、e project in conformance with ECSS-S-ST-00. BS EN 16603-50-02:2014EN 16603-50-02:2014 (E) 7 2 Normative references The following normative documents contain provisions which, through reference in this text, constitute provisions of this ECSS Standard. For dated references, subsequent amendments to,

31、or revisions of any of these publications, do not apply. However, parties to agreements based on this ECSS Standard are encouraged to investigate the possibility of applying the most recent editions of the normative documents indicated below. For undated references the latest edition of the publicat

32、ion referred to applies. EN reference Reference in text Title EN 16601-00-01 ECSS-S-ST-00-01 ECSS system Glossary of terms EN 16603-50 ECSS-E-ST-50 Space engineering Communications EN 16603-50-05 ECSS-E-ST-50-05 Space engineering Radio frequency and modulation BS EN 16603-50-02:2014EN 16603-50-02:20

33、14 (E) 8 3 Terms, definitions and abbreviated terms 3.1 Terms from other standards For the purpose of this Standard, the terms and definitions from ECSS-S-ST-00-01 and ECSS-E-ST-50 apply. 3.2 Terms specific to the present standard 3.2.1 category A category of those spacecraft having an altitude abov

34、e the Earths surface of less than 2 106km 3.2.2 category B category of those spacecraft having an altitude above the Earths surface equal to, or greater than, 2 106km 3.3 Abbreviated terms For the purpose of this Standard, the abbreviated terms from ECSS-S-ST-00-01 apply: Abbreviation Meaning AGC au

35、tomatic gain control AU astronomical unit 2BL double-sided phase locked loop noise bandwidth BPSK binary phase shift keying (see PSK) CCSDS Consultative Committee for Space Data Systems CLCW command link control word C/N carrier to noise ratio dB decibel dBc dB with respect to the unmodulated carrie

36、r DRVID differenced range versus integrated Doppler BS EN 16603-50-02:2014EN 16603-50-02:2014 (E) 9 IF intermediate frequency LO local oscillator NRZ non-return to zero NRZ-L NRZ-level PCM pulse code modulation PLL phase-locked loop PM phase modulation PSK phase shift keying Pp peak to peak RF radio

37、 frequency r.m.s. root-mean-square SNR signal-to-noise ratio SPE static phase error SP-L split phase-level TC telecommand TM telemetry TR tracking UTC universal time (coordinated) BS EN 16603-50-02:2014EN 16603-50-02:2014 (E) 10 4 Requirements 4.1 Functional 4.1.1 Functional breakdown The ranging an

38、d Doppler tracking system is a spacecraft tracking system capable of providing information on the range and range rate between a spacecraft and an Earth station. It uses an active transponder on-board the spacecraft for the retransmission to the ground of an Earth-to-Space link signal: ranging signa

39、l generation and measurement are performed in the Earth station. As a baseline, it is assumed that the spacecraft transponder is used not only for ranging purposes, but also for receiving telecommand signals from Earth and for transmitting telemetry signals to Earth modulated on the same RF carriers

40、. When a transponder is used exclusively for ranging, the requirements in this standard concerning sharing with telecommand and telemetry have no relevance. A functional breakdown of the ranging and Doppler tracking system is presented in Figure 4-1. It depicts the five major functions of the system

41、, broken down into functional blocks, as follows: The Earth-to-Space link function, employing ground communication, process control, ranging signal generation and Earth-to-Space communication. NOTE Ground communication between the Earth station and the Control Centre is not part of the present Stand

42、ard. The transponder function, either spacecraft transponder or ground-calibration transponder depending on the application. The Space-to-Earth link function, employing Space-to-Earth communica-tion, Doppler measurement, ranging replica generation, ranging correla-tion, process control and ground co

43、mmunication. The link-control function, resident partly in the Space-to-Earth and Earth-to-Space communication and partly in the process control. The data-acquisition function, concerned with collection, measurement, processing and transfer of data to the control centre, employing the process-contro

44、l and the ground communication functions. The requirements relevant to these five major functions are listed in clauses 4.1.2 to 4.1.6. BS EN 16603-50-02:2014EN 16603-50-02:2014 (E) 11 GROUND STATIONPROCESSCONTROLDOPPLERMEASUREMENTREPLICACORRELATIONGENERATIONSIGNALGENERATIONCOMMUNICATIONGROUNDEARTH-

45、SPACECOMMUNICATIONSPACECRAFTRECEIVERSPACECRAFTTRANSMITTERTRANSPONDERSPACE-EARTHCOMMUNICATIONSPACECRAFTCoherentCarrierTransfer(CoherentMode only)RangingTelecommandReference FrequencyReferenceTimingRANGINGRANGINGRANGINGCALIBRATIONGROUNDDOPPLER telemetry; ranging and telemetry; none of the above (for s

46、pecific missions requiring Doppler measurement of high accuracy, whereby an unmodulated carrier is used). BS EN 16603-50-02:2014EN 16603-50-02:2014 (E) 13 7. Modulation of the carrier. 8. Up-conversion of the modulated carrier to the assigned Space-to-Earth link frequency. 9. Transmission to Earth.

47、4.1.3.2 Ground calibration transponder a. The ground calibration transponder function shall consist of the following: 1. Frequency conversion of the RF signal from the Earth-to-Space link carrier frequency to the Space-to-Earth link carrier frequency for the purpose of calibrating the ground equipme

48、nt delay. NOTE The ranging calibration measurement is usually performed before and after ranging operations with the spacecraft. 2. Frequency conversion of the RF signal from the Earth-to-Space link carrier frequency to the Space-to-Earth link carrier frequency for verification of Earth station phas

49、e stability. 4.1.4 Space-to-Earth link function a. The Space-to-Earth link function shall consist of the following: 1. Reception and amplification of the spacecraft signal. 2. Down conversion to an IF band, by means of local oscillators coherent with the station reference frequency or with the Earth receiver phase-locked reference. 3. Phase tracking of the IF signal. 4. Automatic gain control. 5. Reception of telemetry for transponder delay correction, if used NOTE The following housekeeping information which is embedded in the telemetry data s