ETSI TS 102 188-6-2004 Satellite Earth Stations and Systems (SES) Regenerative Satellite Mesh - A (RSM-A) air interface Physical layer specification Part 6 Radio link control (V1 1.pdf

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1、 ETSI TS 102 188-6 V1.1.2 (2004-07)Technical Specification Satellite Earth Stations and Systems (SES);Regenerative Satellite Mesh - A (RSM-A) air interface;Physical layer specification;Part 6: Radio link controlETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 2 Reference RTS/SES-00208-6 Keywords air interfac

2、e, broadband, IP, multimedia, satellite ETSI 650 Route des Lucioles F-06921 Sophia Antipolis Cedex - FRANCE Tel.: +33 4 92 94 42 00 Fax: +33 4 93 65 47 16 Siret N 348 623 562 00017 - NAF 742 C Association but non lucratif enregistre la Sous-Prfecture de Grasse (06) N 7803/88 Important notice Individ

3、ual copies of the present document can be downloaded from: http:/www.etsi.org The present document may be made available in more than one electronic version or in print. In any case of existing or perceived difference in contents between such versions, the reference version is the Portable Document

4、Format (PDF). In case of dispute, the reference shall be the printing on ETSI printers of the PDF version kept on a specific network drive within ETSI Secretariat. Users of the present document should be aware that the document may be subject to revision or change of status. Information on the curre

5、nt status of this and other ETSI documents is available at http:/portal.etsi.org/tb/status/status.asp If you find errors in the present document, send your comment to: editoretsi.org Copyright Notification No part may be reproduced except as authorized by written permission. The copyright and the fo

6、regoing restriction extend to reproduction in all media. European Telecommunications Standards Institute 2004. All rights reserved. DECTTM, PLUGTESTSTM and UMTSTM are Trade Marks of ETSI registered for the benefit of its Members. TIPHONTMand the TIPHON logo are Trade Marks currently being registered

7、 by ETSI for the benefit of its Members. 3GPPTM is a Trade Mark of ETSI registered for the benefit of its Members and of the 3GPP Organizational Partners. ETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 3 Contents Intellectual Property Rights4 Foreword.4 1 Scope 5 2 References 5 3 Definitions and abbreviati

8、ons.5 3.1 Definitions5 3.2 Abbreviations .5 4 General description of radio link control system .6 5 ST antenna initial pointing .7 5.1 Calculating ST Antenna Elevation and Azimuth Angles .7 6 Selection of Cell/Microcell and Beam Polarization .8 6.1 Conversion of geodetic LLA coordinates to antenna c

9、oordinates system8 6.2 Cell selection10 6.3 Microcell selection .10 6.4 Downlink Destination ID .11 7 System information reception 11 8 RF uplink power control.12 8.1 Burst probing power.12 8.2 Power control maintenance 12 8.3 ULPC information13 8.3.1 SNR 13 8.3.2 Block Decoder Metric.13 8.3.3 Uplin

10、k noise measurement14 9 Radio link failure14 10 Fallback mode 14 11 Control Parameters.16 11.1 Parameters for installation and cell selection .16 Annex A (informative): Cell parameters17 A.1 General Description17 A.1.1 Antenna boresight angles for North American Satellites .17 A.1.2 Cell definition,

11、 mapping, polarization, and unique word assignment 17 A.1.3 Downlink destination ID 19 A.1.4 Downlink microcell polarization assignments20 Annex B (informative): Bibliography.21 History 22 ETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 4 Intellectual Property Rights IPRs essential or potentially essential

12、to the present document may have been declared to ETSI. The information pertaining to these essential IPRs, if any, is publicly available for ETSI members and non-members, and can be found in ETSI SR 000 314: “Intellectual Property Rights (IPRs); Essential, or potentially Essential, IPRs notified to

13、 ETSI in respect of ETSI standards“, which is available from the ETSI Secretariat. Latest updates are available on the ETSI Web server (http:/webapp.etsi.org/IPR/home.asp). Pursuant to the ETSI IPR Policy, no investigation, including IPR searches, has been carried out by ETSI. No guarantee can be gi

14、ven as to the existence of other IPRs not referenced in ETSI SR 000 314 (or the updates on the ETSI Web server) which are, or may be, or may become, essential to the present document. Foreword This Technical Specification (TS) has been produced by ETSI Technical Committee Satellite Earth Stations an

15、d Systems (SES). The present document is part 6 of a multi-part deliverable covering the BSM Regenerative Satellite Mesh - A (RSM-A) air interface; Physical layer specification, as identified below: Part 1: “General description“; Part 2: “Frame structure“; Part 3: “Channel coding“; Part 4: “Modulati

16、on“; Part 5: “Radio transmission and reception“; Part 6: “Radio link control“; Part 7: “Synchronization“. ETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 5 1 Scope The present document presents the requirements for synchronizing timing and frequency between the ST and the satellite network within the SES BS

17、M Regenerative Satellite Mesh - A (RSM-A) air interface family. 2 References Void. 3 Definitions and abbreviations 3.1 Definitions For the purposes of the present document, the following terms and definitions apply: Network Control Centre (NCC): centre that controls the access of the satellite termi

18、nal to an IP network and also provides element management functions and control of the address resolution and resource management functionality satellite payload: part of the satellite that provides air interface functions NOTE: The satellite payload operates as a packet switch that provides direct

19、unicast and multicast communication between STs at the link layer. Satellite Terminal (ST): terminal installed in the user premises terrestrial host: entity on which application level programs are running NOTE: It may be connected directly to the Satellite Terminal or through one or more networks. 3

20、.2 Abbreviations For the purposes of the present document, the following abbreviations apply: DDID Downlink Destination ID EIRP Effective Isotropic Radiated Power IP Internet Protocol LLA Latitude, Longitude and Altitude Mbps Mega bits per second (millions of bits per second) MIP Management Informat

21、ion Packet MMI Man-Machine Interface NCC Network Control Centre PCESTDPower Control Error Standard PHY PHYsical PTP Point-to-Point RS Reed-SolomonRSM Regenerative Satellite Mesh SLC Satellite Link Control ST Satellite Terminal TDMA Time Division Multiple Access TIP Transmission Information Packet UL

22、PC UpLink Power Control UW Unique Word ETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 6 4 General description of radio link control system BSM RSM-A is a multi-spot beam, multicarrier, synchronous system where the timing and frequency on the satellite serve as the reference to synchronize the TDMA transmis

23、sions for the STs, and other network elements. The satellite includes a packet switch designed to provide single-hop, point to point packet routing between downlink cells. The functions of the physical layer are different for the uplink and downlink. The major functions are illustrated in figure 4.

24、UPLINK DOWNLINK Part 3: Channel coding Part 2: Frame structure Part 4: Modulation Part 5: Radio transmission and reception tn Part 7: Synchronization Block interleaving Inner coding (convolutional) Downlink burst building Downlink modulation (QPSK) ST receiver Scrambling Assemble packets into code b

25、locks Outer coding (Reed-Solomon) No interleaving Inner coding (hamming) Uplink burst building Uplink modulation (OQPSK) Part6:Radiolink controlScrambling Timing and frequency control ST transmitter Assemble packets into code blocks Outer coding (Reed-Solomon) Figure 4: Physical layer functions The

26、present document describes the radio link control functions. This group of functions is highlighted in figure 4. Clause 5 describes ST antenna pointing. Clause 6 describes cell and microcell selection. Clause 7 describes system information reception. Clause 8 describes power control. Clause 9 descri

27、bes radio link failure. Clause 10 describes fallback mode of operation and transition requirements. Clause 11 describes radio link measurements. Clause 12 describes the control parameters required to perform radio link control. ETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 7 Clauses 5 and 6 describe the p

28、rocedures used for installation of the ST. These procedures require knowledge of the ST location and also the location and cell parameters of the desired RSM-A satellite. This information may be obtained by any suitable combination of internal and external mechanisms, provided that the resulting acc

29、uracy complies with the requirements given in the present document. The calculations in the present document assume ST location in the form of the ST Latitude, Longitude and Altitude (LLA). The ST may have an integrated GPS receiver or may have a suitable Man-Machine Interface (MMI) such that the in

30、formation may be entered into the ST by an installer. Alternatively, some GPS receivers can output in earth centred earth fixed (ECEF) Cartesian coordinates. Required accuracy of LLA is given in RSM-A; Air Interface; Physical layer specification, TS 102 188-7. The details of the MMI are outside the

31、scope of the present document. 5 ST antenna initial pointing In order to determine the proper initial pointing of an ST antenna, the ST antenna elevation angle and azimuth angle shall be calculated from knowledge of the ST position and the location of the desired RSM-A satellite. 5.1 Calculating ST

32、Antenna Elevation and Azimuth Angles The inputs to this procedure are the Satellite location and the ST location information. These calculations assume the ST location information, the geodetic latitude and longitude (ST_LAT and ST_LONG), are known. The Geodetic coordinate system is the coordinate s

33、ystem which uses the Prime Meridian and the Equator as the reference planes to define the latitude and longitude. The geodetic latitude of a point is the angle from the equatorial plane to the vertical direction of a line normal to the reference ellipsoid. The geodetic longitude of a point is the an

34、gle between a reference plane and a plane passing through the point, both planes being perpendicular to the equatorial plane. The geodetic height at a point is the distance from the reference ellipsoid to the point in a direction normal to the ellipsoid. The geodetic height of the ST shall be requir

35、ed in the calculations performed in clause 6. In order to determine the ST latitude, longitude and height, as required to perform the calculations in this clause and clause 6, the ST may have an integrated GPS receiver or may have a suitable Man-Machine Interface (MMI) such that the information may

36、be entered into the ST by an installer. Alternatively, any other algorithm may be used to locate an ST provided that the timing requirements described in BSM RSM-A physical layer specification, TS 102 188-7 and cell selection requirements can be met. The ST may calculate the ST antenna elevation and

37、 azimuth pointing angles or may use any other algorithm to locate an ST provided that the ST may be pointed accurately so as to meet the transmitter and receiver requirements in RSM-A physical layer specification, TS 102 188-5. The ST may have a lookup table listing all the satellite locations or th

38、is may be information entered at the time of installation. Since there may be new BSM RSM-A systems in the future, an ST manufacturer should have a method whereby an ST might be located anywhere in the world and use any BSM RSM-A satellite which may be in view of that location. The ST Elevation angl

39、e (ST_EL) and the ST azimuth angle (ST_AZ) are computed as follows: Sin ( ) = cos (ST_LAT) cos (Long) ye= sin - RC/ Rgeoxe= cos () ST_EL = tan-1(ye/ xe) ya= -sin (Long) xa= -sin (ST_LAT) cos (Long) ST_AZ = tan-1(ya/ xa ) ETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 8 where RC= a/K and where a is the radi

40、us of the earth. K is a latitude dependent constant given by: K = (1 - F (2 - F) sin2(ST_LAT)1/2The parameter Rgeois the geosynchronous orbit radius. The parameter F is the flattening defined by: F = (a - b) / a where a is the semi-major earth axis (ellipsoid equatorial radius) and b is the semi-min

41、or earth axis (ellipsoid polar radius); and Long is the angular difference between the satellite location and the geodetic longitude location of the ST. Long = -ST_LONG where is the orbital location in degrees longitude West and ST_LONG is the terminal location is degrees longitude West. Table A.1.1

42、 lists the RSM-A satellite positions for North America. Note that all trigonometric calculations should be in radians. If the ST performs these calculations, the pointing angles shall be saved in non-volatile memory and output through a suitable MMI to the installer to use for initial antenna pointi

43、ng. 6 Selection of Cell/Microcell and Beam Polarization 6.1 Conversion of geodetic LLA coordinates to antenna coordinates system These calculations determine the slant path (distance from satellite to ST) and help determine the cell and microcell based on the ST position. First transform the latitud

44、e and longitude to the Cartesian coordinate systems (Xp, Yp, Zp) as shown in figure 6.1. The coordinate system is shifted by the geosynchronous radius in order to place the origin at the centre of the Earth. The elements of vector (Xp, Yp, Zp) are computed as follows Given the ST location in geodeti

45、c coordinates (Height, Latitude and Longitude) the following procedure will convert them to Cartesian coordinates (X, Y, Z). The elements of the ST location (in Cartesian coordinates) are computed as follows: XST= (RC + height) cos (ST_LAT) cos (Long) YST= (RC+ height) cos (ST_LAT) sin (Long) ZST= (

46、RC(1-F)2+ height) sin (ST_LAT) Xp= XST- Rgeo Yp= YST, and p= ZSTETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 9 NorthPoleStationLocationEquatorSub-SatellitePointLongReElAzLatZpXp YpSatelliteLocationFigure 6.1: On-orbit geometry The vector (Xp, Yp, Zp) is placed into a rotated coordinate system to take int

47、o account the boresight pointing of the antenna. This rotation is performed through the following linear equation: =pppZYXMZYXwhere M is a rotation matrix given by: =1000)cos()sin(0)sin()cos()cos(0)sin(010)sin(0)cos(XXXXYYYYM Xis the boresight azimuth angle and Yis the boresight elevation angle defi

48、ned in annex A. Finally, compute the azimuth and elevation angles. += =2211tantanYXZElXYAzwhere Az and El are the ST angular coordinates relative to the satellite boresight. ETSI ETSI TS 102 188-6 V1.1.2 (2004-07) 106.2 Cell selection At installation, after mapping the ST position into satellite ant

49、enna (Az, El) coordinates, the ST may use a look-up table to determine cell, and uplink polarization, microcell and downlink polarization, and downlink destination IDs to be used at that location. Example look-up tables are presented in annex A for some RSM-A systems. Because the coverage grids used are hexagonal in angle space, the cell (or microcell) centre closest to this point defines the cell (or microcell) location for the ST. Alternatively, this information may be entered into the termin