TIA-1040 1 06-2005 Regenerative Satellite Mesh-A (RMS-A) Air Interface - Physical Layer Specification - Part 6 Radio Link Control《再生卫星Mesh-A (RMS-A)空中接口 物理层规范第6部分 无线电链路控制》.pdf

《TIA-1040 1 06-2005 Regenerative Satellite Mesh-A (RMS-A) Air Interface - Physical Layer Specification - Part 6 Radio Link Control《再生卫星Mesh-A (RMS-A)空中接口 物理层规范第6部分 无线电链路控制》.pdf》由会员分享，可在线阅读，更多相关《TIA-1040 1 06-2005 Regenerative Satellite Mesh-A (RMS-A) Air Interface - Physical Layer Specification - Part 6 Radio Link Control《再生卫星Mesh-A (RMS-A)空中接口 物理层规范第6部分 无线电链路控制》.pdf（26页珍藏版）》请在麦多课文档分享上搜索。

1、 TIA STANDARD Regenerative Satellite Mesh-A (RMS-A) Air Interface - Physical Layer Specification - Part 6: Radio Link Control TIA-1040.1.06 April 2005 TELECOMMUNICATIONS INDUSTRY ASSOCIATION The Telecommunications Industry Association represents the communications sector of NOTICE TIA Engineering St

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16、ATIONS. TIA 1040.1.06 1Contents Intellectual Property Rights4 Foreword 4 1 Scope5 2 References5 3 Definitions and abbreviations 5 3.1 Definitions. 5 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 Azi

17、muth Angles. 7 6 Selection of Cell/Microcell and Beam Polarization.8 6.1 Conversion of geodetic LLA coordinates to antenna coordinates system. 8 6.2 Cell selection. 10 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 p

18、robing power . 12 8.2 Power control maintenance. 12 8.3 ULPC information. 13 8.3.1 SNR . 13 8.3.2 Block Decoder Metric. 13 8.3.3 Uplink noise measurement 14 9 Radio link failure14 10 Fallback mode 14 11 Control Parameters.16 11.1 Parameters for installation and cell selection. 16 Annex A (informativ

19、e): Cell parameters17 A.1 General Description .17 A.1.1 Antenna boresight angles for North American Satellites. 17 A.1.2 Cell definition, mapping, polarization, and unique word assignment . 17 A.1.3 Downlink destination ID. 19 A.1.4 Downlink microcell polarization assignments . 20 Annex B (informati

20、ve): Bibliography.21 History22 TIA 1040.1.06 2 Intellectual Property Rights IPRs essential or potentially essential 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 f

21、ound in ETSI SR 000 314: “Intellectual Property Rights (IPRs); Essential, or potentially Essential, IPRs notified to 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

22、 the ETSI IPR Policy, no investigation, including IPR searches, has been carried out by ETSI. No guarantee can be given 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.

23、Foreword This Technical Specification (TS) has been produced by ETSI Technical Committee Satellite Earth Stations and 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 ide

24、ntified below: Part 1: “General description“; Part 2: “Frame structure“; Part 3: “Channel coding“; Part 4: “Modulation“; Part 5: “Radio transmission and reception“; Part 6: “Radio link control“; Part 7: “Synchronization“. TIA 1040.1.06 31 Scope The present document presents the requirements for sync

25、hronizing timing and frequency between the ST and the satellite network within the SES BSM 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 ap

26、ply: Network Control Centre (NCC): centre that controls the access of the satellite terminal 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 interfac

27、e functions NOTE: The satellite payload operates as a packet switch that provides direct 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:

28、It may be connected directly to the Satellite Terminal or through one or more networks. 3.2 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

29、 Altitude Mbps Mega bits per second (millions of bits per second) MIP Management Information Packet MMI Man-Machine Interface NCC Network Control Centre PCESTDPower Control Error Standard PHY PHYsical PTP Point-to-Point RS Reed-Solomon RSM Regenerative Satellite Mesh SLC Satellite Link Control ST Sa

30、tellite Terminal TDMA Time Division Multiple Access TIP Transmission Information Packet ULPC UpLink Power Control UW Unique WordTIA 1040.1.06 4 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 sa

31、tellite serve as the reference to synchronize the TDMA transmissions 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

32、and downlink. The major functions are illustrated in figure 4. UPLINK DOWNLINKPart 3: Channel coding Part 2: Frame structure Part 4: Modulation Part 5: Radio transmission and reception tnPart 7: Synchronization Block interleavingInner coding (convolutional)Downlink burstbuildingDownlink modulation (

33、QPSK)ST receiverScramblingAssemble packetsinto code blocksOuter coding (Reed-Solomon)No interleavingInner coding(hamming)Uplink burstbuildingUplink modulation(OQPSK)Part6:RadiolinkcontrolScramblingTiming and frequency controlST transmitterAssemble packetsinto code blocksOuter coding (Reed-Solomon)Fi

34、gure 4: Physical layer functions The 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 des

35、cribes power control. Clause 9 describes 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. TIA 1040.1.06 5Clauses 5 and 6 desc

36、ribe the procedures 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 res

37、ulting accuracy 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 t

38、hat the information 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 ou

39、tside the 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 Calcu

40、lating ST 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 co

41、ordinate system 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

42、 is the angle 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

43、 be required 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 inform

44、ation may 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 ele

45、vation and 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 locat

46、ions or this 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 Elev

47、ation angle (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 ) TIA 1040.1.06 6 where RC= a/K and where a is the radius of the earth.

48、 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-minor earth axis (e

49、llipsoid 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 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 poi