ITU-R M 1828-2007 Technical and operational requirements for aircraft stations of aeronautical mobile service limited to transmissions of telemetry for flight testing in the bands .pdf

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1、 Rec. ITU-R M.1828 1 RECOMMENDATION ITU-R M.1828 Technical and operational requirements for aircraft stations of aeronautical mobile service limited to transmissions of telemetry for flight testing in the bands around 5 GHz (2007) Scope This Recommendation provides the technical and operational requ

2、irements for aircraft stations of aeronautical mobile service limited to transmissions of telemetry for flight testing that should be used by administrations as a technical guideline for establishing conformance requirements for aircraft stations for worldwide use. The ITU Radiocommunication Assembl

3、y, considering a) that various technically and operationally different aeronautical mobile service (AMS) limited to transmissions of telemetry systems for flight testing networks have been designed to commence operation in the near future; b) that the operation of aircraft station is usually a subje

4、ct of a number of national and international rules and regulations including satisfactory conformance to a mutually agreed technical standard and operational requirements; c) that there is a need for identifying the technical and operational requirements for the conformance testing of aircraft stati

5、ons; d) that the identification of technical and operational requirements for aircraft stations would provide a common technical basis for facilitating conformance testing of aircraft station by various national and international authorities and the development of mutual recognition arrangements for

6、 conformance of aircraft stations; e) that the technical and operational requirements need to achieve an acceptable balance between radio equipment complexity and the need for effective use of the radio-frequency spectrum, considering also a) that in the frequency band 5 150-5 250 MHz there are allo

7、cations to aeronautical radionavigation, fixed-satellite (Earth-to-space) and mobile services on a primary basis; b) that there is a requirement to fully protect all primary services in the band 5 030-5 250 MHz; c) that WRC-03 adopted Resolution 229 which governs use of band 5 150-5 250 MHz by the m

8、obile service for the implementation of wireless access systems (WAS) including radio local area networks (RLANs); d) that the identification by ITU-R of technical and operational requirements for aircraft stations operating in the band 5 030-5 250 MHz should prevent unacceptable interference to oth

9、er services; 2 Rec. ITU-R M.1828 e) that technical and operational characteristics should be continuously and accurately measurable and controllable; f) that the band 5 030-5 150 MHz is allocated to the aeronautical radionavigation service on a primary basis; g) that the MLS can be protected through

10、 the implementation of an adequate separation distance between a radiating aeronautical mobile service (AMS) transmitter to support telemetry and MLS receivers; h) that the ITU-R is in the process of developing guidance material on the application of the methodology described in Recommendation ITU-R

11、 M.1829, recognizing a) that the band 5 030-5 150 MHz is to be used for the operation of the international standard microwave landing system (MLS) for precision approach and landing; the requirements for this system shall take precedence over other uses of this band in accordance with No. 5.444 of t

12、he Radio Regulations (RR), recommends 1 that the technical and operational requirements for aircraft stations of AMS limited to transmissions of telemetry for flight testing operating in the 5 GHz band given in Annexes 1 and 2 should be used by administrations as guidelines to facilitate compatibili

13、ty with other services; 2 that all aircraft stations of AMS limited to transmissions of telemetry for flight testing and transmitting simultaneously within one AMS network should use non-overlapping spectrum. Annex 1 Technical and operational requirements for aircraft stations of AMS limited to tran

14、smissions of telemetry system for flight testing networks in the bands around 5 GHz Part A Essential requirements related to the protection of FSS networks in the band 5 091-5 250 MHz An aircraft station of AMS in the band 5 091-5 250 MHz should be designed in such a manner that one aircraft station

15、 transmitter power flux-density be limited to 138 dB(W/(m2 1.23 MHz) at the FSS satellite orbit for spacecraft using full Earth coverage receive antennas. The maximum aggregate interference level of 1% Ts/Tstolerable at the receiver input is IAgg-Rec: MHz)23.1/dB(W3.160dB20 =KTBIRecAggRec. ITU-R M.1

16、828 3 where: K: Boltzmanns constant (1.38 e-23) T: represents the receiver noise temperature: 550 K B: receiver bandwidth: 1.23 MHz. Therefore at the satellite receiver antenna input the maximum pfd level produced by one AMT transmitter is: )MHz23.1m/(dBW1386.352.1319.243.1604log10)21(log102210=+=+=

17、 PFeedRecAggMaxLLGrIpfdwhere: Gr: FSS receiver antenna gain 21: maximum number of AMT station emitting simultaneously in the FSS receiver bandwidth. NOTE 1 The aforementioned limit relate to the pfd would be obtained under free-space propagation conditions. NOTE 2 An e.i.r.p. mask can be derived fro

18、m the aforementioned pfd value by applying the method given in Part A of Annex 2. Simplification of the resulting e.i.r.p. mask could also be considered. NOTE 3 The afore-mentioned limit corresponds to 198.9 dB(W/(m2 Hz). NOTE 4 The pfd limit defined in this section is based on ensuring that the inc

19、rease in noise temperature of the FSS satellite (i.e. Tsat/Tsat) due to operation of the AMT does not exceed 1%. The methodology assumes 21 co-channel AMT transmitters operating concurrently within the field of view of the FSS satellite. Part B Essential requirements related to the protection of the

20、 mobile service in the band 5 150- 5 250 MHz The essential requirements which follow only represent a technical guideline. In the 5 150-5 250 MHz frequency band, the maximum pfd produced at the surface of the Earth by emissions from an aircraft station, of an AMS system limited to transmissions of t

21、elemetry for flight testing network should not exceed: 79.4 dB(W/(m2 20 MHz) Gr(). Administrations may choose to implement different AMS technical and operational requirements which are more stringent than those referenced in this section to protect the mobile service. Further study may be necessary

22、 if different parameters are used than those assumed in developing this guideline. 4 Rec. ITU-R M.1828 Gr() represents the mobile service receiver antenna pattern versus elevation angle and is defined as follows: Wireless access system elevation antenna pattern Elevation angle, (degrees) Gain (dBi)

23、45 90 4 35 45 3 0 35 0 15 0 1 30 15 4 60 30 6 90 60 5 where: Gr(): gain relative to an isotropic antenna (dBi) : absolute value of the elevation angle relative to the angle of maximum gain (degrees) FIGURE 1 Mobile service receiver antenna pattern NOTE 5 The aforementioned limits relate to the pfd a

24、nd angles of arrival that would be obtained under free-space propagation conditions. Rec. ITU-R M.1828 5 NOTE 6 An e.i.r.p. mask can be derived from the aforementioned pfd mask by applying the method given in Part B of Annex 2. Simplification of the resulting e.i.r.p. mask could also be considered.

25、Part C Essential requirements related to the protection of the aeronautical mobile (route) service (AM(R)S) in the band 5 091-5 150 MHz The AM(R)S receiver characteristics based on IEEE 802.16e standard and ITU-R Recommendations taken into account in this sharing study are as follow: Protection crit

26、eria: I/N of 6 dB as expressed in Recommendation ITU-R M.1739 and which corresponds to a range reduction of 5%. Receiver noise factor: 10 dB. Implementation loss: 5 dB. Building loss: 0 dB (outdoor usage). Receiver bandwidth: 20 MHz. Antenna pattern: The AM(R)S receiver antenna gain versus elevation

27、 angle pattern considered in the analysis is adopted from the Recommendation ITU-R F.1336-1 and shown in Fig. 2. Peak gain is assumed to be 6 dBi. In the 5 091-5 150 MHz frequency band, the maximum pfd produced at the surface of the Earth by emissions from an aircraft stations, of an AMS system limi

28、ted to transmissions of telemetry for flight testing network should not exceed: 89.4 dB(W/(m2 20 MHz) Gr(). Gr() represents the mobile service receiver antenna pattern versus elevation angle and is defined as follows: )(),(max)(21= GGGr2127126)(=G + +=7.01,27maxlog106)(5.12G where: G(): gain relativ

29、e to an isotropic antenna (dBi) : absolute value of the elevation angle (degrees) The pfd and the resultant EIRP mask are provisional, and need to be confirmed when the AM(R)S is more fully developed. 6 Rec. ITU-R M.1828 FIGURE 2 AM(R)S receiver antenna pattern NOTE 7 The aforementioned limits relat

30、e to the pfd and angles of arrival that would be obtained under free-space propagation conditions. NOTE 8 An e.i.r.p. mask can be derived from the aforementioned pfd mask by applying the method given in Part B of Annex 2. Simplification of the resulting e.i.r.p. mask could also be considered. Part D

31、 Essential requirements related to the protection of the aeronautical radionavigation service operating in the band 5 030-5 150 MHz When bilateral coordination is necessary between administrations operating microwave landing systems and administrations operating AMT systems, ITU-R Recommendation pre

32、sented in considering also h) could help for bilateral discussions. Part E Essential requirements related to the protection of the aeronautical security application in the band 5 091-5 150 MHz Studies have shown that where AMS(AS) and AMS(AMT) are not operating overlapping frequencies then frequency

33、 compatibility is achieved and no essential requirements are needed to protect the AMS(AS) application. However, for the overlapping frequency operation, further studies need to be developed. Rec. ITU-R M.1828 7 Annex 2 Derivation of an e.i.r.p. mask from a pfd limit Part A Derivation of a higher he

34、misphere e.i.r.p. mask from a pfd limit In testing AMS equipment limited to transmissions of telemetry for flight testing to determine if it meets a given pfd limit, such as the one in Part A of Annex 1, it may be useful to determine an equivalent e.i.r.p. mask that can be used for testing purposes.

35、 The pfd limit can be used to mathematically determine a higher hemisphere e.i.r.p. mask, e.i.r.p. (, H) where is the angle above the local horizontal plane and H is the altitude of the aircraft. This conversion proceeds in two steps. First, is converted to an equivalent angle below the horizontal a

36、t the satellite, . Then the length of the propagation path for angle above the horizontal is determined and used to calculate the spreading loss for the path and the resulting e.i.r.p. Step 1: Calculation of an angle below the horizontal at the satellite (degrees), , from and H: ()()+=SateeHRHR)cos(

37、arccos where: : angle above the horizontal at the aircraft stations Re:earth radius (6 378 km) H : altitude of the aircraft (km) HSat: altitude of the FSS satellite (km) : angle below horizontal at the satellite. Step 2: Calculation of the e.i.r.p. value from the defined pfd limit: ()( )()( )()2/122

38、cos2sateesateeHRHRHRHRd += 60)4(log10pfd),(e.i.r.p.210+= dH where: d : distance between the aircraft stations and the considered point on the Earths surface (km) pfd : pfd limit (dB(W/(m2 MHz) e.i.r.p. : (dB(W/MHz). Figure 3 shows this function for an aircraft altitudes of 12 km based on the pfd lim

39、it provided in Part A of Annex 1. In this example, Hsatis taken as 1 414 km. 8 Rec. ITU-R M.1828 FIGURE 3 Part B Derivation of a lower hemisphere e.i.r.p. mask from a pfd limit In testing AMS equipment limited to transmissions of telemetry for flight testing to determine if it meets a given pfd limi

40、t, such as the one in Part B of Annex 1, it may be useful to determine an equivalent e.i.r.p. mask that can be used for testing purposes. The pfd limit can be used to mathematically determine an e.i.r.p. mask, e.i.r.p. (, H) where is the angle below the local horizontal plane and H is the altitude o

41、f the aircraft. This conversion proceeds in two steps. First, is converted to an equivalent angle of arrival, . Then the length of the propagation path for angle of arrival is determined and used to calculate the spreading loss for the path and the resulting e.i.r.p. Step 1: Calculation of an angle

42、of arrival in degrees, , from and H: )/)cos()arccos(eeRHR += where: : angle of arrival Re:earth radius (6 378 km) H : altitude of the aircraft (km) : angle below horizontal. NOTE 1 If the argument of the arccos function is greater than 1, the propagation path in the direction of the angle does not i

43、ntersect the Earth. In this case, which occurs for values of of about 3.5 or less, a value for does not exist and so there is no defined value for the pfd mask. Rec. ITU-R M.1828 9 Step 2: Calculation of the e.i.r.p. value from the defined pfd limit: 2/122)cos()(2)( += HRRHRRdeeee60)4(log10pfd),(e.i.r.p.210+= dH where: d : distance between the aircraft stations and the considered point on the Earths surface (km) pfd : pfd limit (dB(W/(m2 MHz) e.i.r.p. : (dB(W/MHz). Figure 4 shows this function for various aircraft altitudes based on the pfd limit provided in Part B of Annex 1. FIGURE 4