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US Radiocommunications SectorFact Sheet

Working Party: WP 5B Document No: USWP5B20-13_Final Draft

Ref: Annex 18 to 5B/411 Date; 2nd April 2018

Author(s)/Contributors(s):

Don NellisFederal Aviation Administration800 Independence Ave., S.W.Washington, DC 20591

Michael NealeACES Corporation for the FAA

Phone/Email:

Phone: (202) 267-9779e-mail: [email protected]

Phone: (858) 705-8978e-mail: [email protected]

Purpose/Objective: The purpose of this contribution is to re-present the contribution that was carried over from the November 2017 meeting (Annex 18 of 5B/411) of WP 5B. The attached is the WP 5B chairman’s merge of all of the contributions to this report that were not discussed in November. No changes (other than to Document references in the Introduction section 1.0) are proposed to the US contribution (Annex 1). The purpose of this contribution is to propose parameter values for the characteristics of CNPC links intended to be supported by the FSS. It will help answer the liaison requests from ICAO (5B/115 and 5B/116) from the November 2016 meeting of WP 5B and the reply from WP 5B (Annex 35 to 5B/195). It supports Resolution 155 (WRC-15) that calls for the need to consider ICAO’s progress (Resolves 18) in developing SARPs and the ITU-R’s completion of technical studies (Resolves 19) and also addresses the new Draft Guidelines for the implementation of Resolution 155 (WRC 15) Annex 28 to 5B/411.

Abstract: This contribution both answers ICAO’s need for characteristics of the CNPC links supported by the FSS to help support their safety and performance based development of regulations (SARPs) as well as the need to comply with a of number resolves (5, 6, 7, 8, 9, 10, 11, 12,14,15, 16, 17) in Resolution 155 (WRC-15). ICAO’s liaison to WP 5B (5B/115 and 5B/116) in November 2016 provided a list of required parameters. This contribution provides values for the parameters directly associated with the links between the UA and UACS Earth stations and the space station (Link1, 2, 3 and 4). This

/TT/FILE_CONVERT/5F8DF87730F77B623712CECF/DOCUMENT.DOCX ( )

Document Title:

WORKING DOCUMENT TOWARDS A PRELIMINARY DRAFT NEW [RECOMMENDATION] [REPORT] ITU-R M.[UAS CNPC_CHAR]

Characteristics of Unmanned Aircraft System Control and Non-Payload Earth Stations for use with Space Stations operating in the Fixed Satellite

Service

mailto:[email protected]

- 2 -5B/411 (Annex 18)-E

report will then be used, in accordance with the Draft Guidelines for Implementation of Resolution 155 (WRC-15) Annex 28 to 5B/411, to compare the satellite network characteristics (contained in additional report) with these CNPC link characteristics to determine if the CNPC link characteristics fit within the envelope of satellite characteristics so proving that the CNPC links can be used with the FSS.

[Note: This document is a merger of contribution made to this meeting of WP 5B and Annex 17 of the last Chairman’s Report. The meeting has not reviewed the content of this document and hence it cannot be considered as if any agreement has been reached with respect to the text. Additionally, completion of this document needs to be consistent with the “Draft Working Party 5B guideline for the implementation of Resolution 155 (WRC-15)” see Appendix XX to this Chairman’s Report]

1 IntroductionIn accordance with paragraph 5 of the guidelines contained in annex 17 18 to the WP 5B Chairman’s Report (Doc. 5B/ 411 305 ) the following contains a compilation of some characteristics of UAS CNPC link/Earth station received by WP 5B at its recent May/June meetings which have not yet been agreed upon.

1.1 Background

Resolution 155 (WRC-15) resolves, that assignments to stations of geostationary FSS satellite networks operating in the frequency bands 10.95-11.2 GHz (space-to-Earth), 11.45-11.7 GHz (space-to-Earth), 11.7-12.2 GHz (space-to-Earth) in Region 2, 12.2-12.5 GHz (space-to-Earth) in Region 3, 12.5-12.75 GHz (space-to-Earth) in Regions 1 and 3 and 19.7-20.2 GHz (space-to-Earth), and in the frequency bands 14-14.47 GHz (Earth-to-space) and 29.5-30.0 GHz (Earth-to-space), may be used for UAS CNPC Links in non-segregated airspace, provided that the conditions specified in resolves below are met.


Radiocommunication Study Groups

Source: Documents 5B/TEMP/175, 5B/380 (France), 5B/388 (Japan), 5B/351 (USA)

Subject: Merged contributions to [Rec.][Rep.] ITU-R M.[UAS CNPC_CHAR]

Annex 18 toDocument 5B/411-E29 November 2017English only

Annex 18 to Working Party 5B Chairman's Report

WORKING DOCUMENT TOWARDS A PRELIMINARY DRAFT NEW [RECOMMENDATION] [REPORT] ITU-R M.[UAS CNPC_CHAR]

Characteristics of Unmanned Aircraft System Control and Non-Payload Earth Stations for use with Space Stations

operating in the Fixed Satellite Service

https://www.itu.int/md/R15-WP5B-C-0351/en




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14 that, unless otherwise agreed between the administrations concerned, UA CNPC Link Earth stations shall not cause harmful interference to terrestrial services of other administrations (see also Annex 2);

15 that, in order to implement resolves 14 above, power flux-density hard limits need to be developed for UAS CNPC Links; one possible example of such provisional limits to protect the fixed service is provided in Annex 2; subject to agreement between the administrations concerned, that annex may be used for the implementation of this resolution;

16 that the power flux-density hard limits provided in Annex 2 shall be reviewed and, if necessary, revised by the next conference;

[..]

18 to consider the progress obtained by ICAO in the process of preparation of SARPs for UAS CNPC Links, to review this resolution at WRC-23, taking into account the results of the implementation of Resolution 156 (WRC-15), and to take necessary actions as appropriate;

19 that ITU Radiocommunication Sector (ITU-R) studies on technical, operational and regulatory aspects in relation to the implementation of this resolution shall be completed, together with the adoption of relevant ITU-R Recommendations defining the technical characteristics of CNPC Links and conditions of sharing with other services,

Since there are currently no UAS operating using CNPC Links these characteristics are based on:1 The data rates for CNPC Links in the ICAO contribution that were themselves based, in

part, on Recommendation ITU R M.2171.2 The performance of representative FSS space stations operated within the notified and

recorded technical parameters as published by the Radiocommunication Bureau.3 The operational scenarios as described by ICAO in 14 May 2013 (Doc. 5B/269).

4 The research development of an in-house Ka band on-board variable directive antenna for UAS conducted in Japan (System 1), under a government-commissioned research project of the Ministry of Internal Affairs and Communications. Attachment A describes the research and development program for further reference.

Annex 1 to this document contains CNPC Link Characteristics based on 1-3 above. Annex 2 contains information based on 4 above. Finally, Appendix A contains information of the WINDS satellite which was used for the evaluation test of the in-house Ka-band on-board variable directive antenna for UAS conducted in Japan as indicated in 4 above.

Editor’s note: In accordance with contribution from France Doc. 5B/158, this document can provide technical and operational characteristics of UA CNPC earth stations expected from ICAO or/and current UAV operators to conduct studies according to resolves 11 to 17.

Since, according to resolves 5 of Resolution 155 (WRC-15), earth stations on board UA have to operate within the notified parameters of an associated satellite network. One of the major issues is that the effective characteristics of the satellite links of a satellite network depend on the bilateral agreements reached by administrations and are not available at ITU. Indeed, the frequency assignments recorded in the MIFR under RR Article 11 do not fully reflect the outcome of bilateral negotiations taking place during the coordination process of a satellite network under RR Article 9.

[Editor's note: The question of the compliance of the proposed protection ratio with the resolves 11 of Resolution 155 WRC-15, has been raised]

The preliminary analysis of an estimation of interference environment caused by FH (Doc. 5B/195, Annex 28) shows that the protection criteria may not be complied in all situations. However it is set



https://www.itu.int/md/meetingdoc.asp?lang=en&parent=R15-WP5B-C-0158

https://www.itu.int/rec/R-REC-M.2071-1-201702-I/en

- 4 -5B/411 (Annex 18)-E

forth in resolves 11 “that earth stations on board UA shall be designed and operated so as to be able to accept the interference caused by terrestrial services operating in conformity with the Radio Regulations in the frequency bands listed in resolves 1 without complaints under Article 15;”

The proposal is to replace the values protection ratios in the following tables by not applicable.

Indeed, required performance availability to be fully observed by UAV/UAS should be determined by ICAO. Issues related to protection criteria can be dealt with by ITU-R only if required performance availability are provided.]


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ANNEX 1

Since Resolution 155 (WRC-15) focusses on a range of specific frequency bands in all of the following tables in Annex 1 the 10.95-11.2 GHz (space-to-Earth), 11.45-11.7 GHz (space-to-Earth), 11.7-12.2 GHz (space-to-Earth) in Region 2, 12.2-12.5 GHz (space-to-Earth) in Region 3, 12.5-12.75 GHz (space-to-Earth) and 14-14.47 GHz (Earth-to-space) frequency bands will be considered as one group referred to as the 14/11GHz frequency band and the 19.7-20.2 GHz (space-to-Earth), and 29.5-30.0 GHz (Earth-to-space) bands will also be considered as one group referred to as the 30/20GHz band.

Annex 1 contains two lists, one for the 14/11GHz frequency band and the other for the 30/20 GHz frequency band, each containing the same set of characteristic’s parameters and the Appendix 4 to the Radio Regulations reference for the data elements.

Characteristics for different systems are tabulated in columns as well as proposed Maximum and Typical values for the characteristic’s parameter values.

Since there are currently no UAS operating using CNPC Links these characteristics are based on:1 The data rates for CNPC Links in the ICAO contribution that were themselves based, in

part, on Recommendation ITU R M.2171.2 The performance of representative FSS space stations operated within the notified and

recorded technical parameters as published by the Radiocommunication Bureau.3 The operational scenarios as described by ICAO in 14 May 2013 (5B/269).

The characteristic’s parameter values of the proposed characteristics are supported by link budget analysis that maximizes the available link margin (to provide the highest quality link performance for these safety of flight applications) while ensuring the links comply with off-axis e.i.r.p. density (ITU-R S.524 UACS Earth station and S.728 UA Earth station) limits as well as the pfd limits at the Earth’s surface (RR Article 21.16) and operation with space station performances that are representative of FSS space stations operated within the notified and recorded technical parameters as published by the Radiocommunication Bureau.


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14/11 GHz general and space station characteristicsGeneral CNPC Link Parameters AP 4 Data Item Name from Preface Units System 1 Proposed Maximum Value Proposed Typical Value

Telecommand, UACS-to-space station-to-UA (Link 1 and 2)Information data rate C.9.a.4.a mod_char bit_rate kbps 25 10Modulation Type. C.9.a.4.b mod_char nbr_phase 2 2FEC Type. User Dependent and Not Recorded 1/3 1/3Spectral efficiency. User Dependent and Not Recorded 0.25 0.25Eb/No @ 1E-8 BER. User Dependent and Not Recorded dB 4 4Roll-off factor. User Dependent and Not Recorded % 35 35Reference bandwidths. User Dependent and Not Recorded kHz 100 40Protection Ratio - Intra System C.12.a s_beam prot_ratio I/N dB -6 -6Protection Ratio - Inter System C.12.a s_beam prot_ratio I/N dB -9 -9

Telemetry, UA-to-space station-to-UACS (Link 3 and 4)Information data rate C.9.a.4.a mod_char bit_rate kbps 300 70Modulation Type. C.9.a.4.b mod_char nbr_phase 2 2FEC Type. User Dependent and Not Recorded 1/3 1/3Spectral efficiency. User Dependent and Not Recorded 0.25 0.25Eb/No @ 1E-8 BER. User Dependent and Not Recorded dB 4 4Roll-off factor. User Dependent and Not Recorded % 35 35Reference bandwidths. User Dependent and Not Recorded kHz 1 200 280Protection Ratio - Intra System C.12.a s_beam prot_ratio I/N dB -6 -6Protection Ratio - Inter System C.12.a s_beam prot_ratio I/N dB -9 -9

Space Station Characteristics. Transmission Link 2 and 4. Reception Link 1 and 3.Transmission Characteristics for each Link (2 and 4)

Frequency. C.1.a s_beam freq_max GHz 12.75GHz 12.75C.1.b s_beam freq_min GHz 10.95GHz 10.95

3 dB beamwidth. B.3.a.1 s_beam gain degrees 2.5degrees 4e.i.r.p. transmit density. Derived from Maximum transmit power and aggregate bandwidth dBW/1MHz at EOC 35dBW in 1MHz at EOC 33

C.8.d.1 grp pwr_max dBW 50dBW 48C.8.d.2 grp bdwdth_aggr MHz 36MHz 36B.3.a.1 s_beam gain dBi at EOC 36.3dBi at EOC 32.3

Link 2 power flux-density. Calculated from e.i.r.p. transmit density and link budget dB(W/m2) in 1MHz -150.0dB(W/m2) in 4kHz -150.0Link 4 power flux density. Calculated from e.i.r.p. transmit density and link budget dB(W/m2) in 1MHz -157.4dB(W/m2) in 4kHz -157.3

Reception Characteristics for each Link (1 and 3)Frequency. C.1.a s_beam freq_max GHz 14.47 GHz 14.47

C.1.b s_beam freq_min GHz 14.00 GHz 143 dB beamwidth. B.3.a.1 s_beam gain degrees 2.5 4

B.3.a.1 s_beam gain dBi at EOC 36.3 32.3G/T or T C.5.a grp noise_t dBi/K at EOC and K 3.0 & 2137 1.0 & 1348


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14/11 GHz links 1, 2, 3 and 4 characteristicsUACS Earth Station Characteristics (Link 1 and 4) and UA Earth Station Characteristics (Link 3 and 2)

Transmission Characteristic for each Link (1 and 3) AP 4 Data Item Name from Preface System 1 Proposed Maximum Value Proposed Typical ValueLink 1 With 100mm/hr rain on Link 1 With Clear Sky on Link 1

Frequency. C.1.a s_beam freq_max GHz 14.47 14.47C.1.b s_beam freq_min GHz 14 14

Maximum on-axis e.i.r.p. density. Derived from Maximum transmit power, aggregate bandwidth and antenna gain dB(W/40kHz) 75.6 47.7C.8.g.1 grp pwr_max dBW 16.2 -8.6C.8.g.2 grp bdwdth_aggr kHz 100 40C.10.d.3 e_as_stn gain dBi 63.4 56.3

Maximum off-axis e.i.r.p density. Derived from Maximum on-axis e.i.r.p. density and Antenna Pattern dB(W/40kHz) at +/- 2.5degrees 26.3 8.9Antenna diameter B.5.a e_ant gain m 13 6Typical antenna efficiency. B.5.a e_ant gain % 60 55Antenna pattern. B.5.b e_ant bmwdth degrees 0.12 0.25

B.5.c e_ant attch_e dBi at +/-2.5degrees 14.1 17.5Pointing error. B.3.d s_beam pnt_acc degrees 0.03 0.6Pointing method. Not Recorded but must meet Pointing Error tracking tracking trackingPower control. C.8.i emiss pwr_ctrl automatic automatic automatic

Link 3 UA above rain height UA above rain heightFrequency. C.1.a s_beam freq_max GHz 14.47 14.47

C.1.b s_beam freq_min GHz 14 14Maximum on-axis e.i.r.p. density. Derived from Maximum transmit power, aggregate bandwidth and antenna gain dB(W/40kHz) 45.2 39.8

C.8.g.1 grp pwr_max dBW 17.7 9.9C.8.g.2 grp bdwdth_aggr kHz 1 200 280C.10.d.3 e_as_stn gain dBi 42.3 38.4

Maximum off-axis e.i.r.p density. Derived from Maximum on-axis e.i.r.p. density and Antenna Pattern dB(W/40kHz) at +/- 2.5degrees 22.7 23Antenna diameter B.5.a e_ant gain m 1.2 0.8Typical antenna efficiency. B.5.a e_ant gain % 60 55Antenna pattern. B.5.b e_ant bmwdth degrees 1.3 1.9

B.5.c e_ant attch_e dBi at +/-2.5degrees 19.8 21.6Pointing error. B.3.d s_beam pnt_acc degrees 0.2 0.2Pointing method. Not Recorded but must meet Pointing Error automatic automatic automaticPower control. C.8.i emiss pwr_ctrl none none none

Reception Characteristics for each Link (2 and 4)Link 2 UA above rain height UA above rain height

Frequency. C.1.a s_beam freq_max GHz 12.75GHz 12.75C.1.b s_beam freq_min GHz 10.95GHz 10.95

G/T or T. C.10.d.6 e_as_stn noise_t K including, sky, moisture, cloud at 10 degrees elevation

212 212

Antenna diameter B.5.a e_ant gain m 1.2 0.8Typical antenna efficiency. B.5.a e_ant gain % 55 50

C.10.d.3 e_as_stn gain dBi 4100% 3700%Antenna patterns. B.5.b e_ant bmwdth degrees 1.5 2.2

B.5.c e_ant attch_e dBi at +/-2.5degrees 18.3 19.6Pointing error. B.3.d s_beam pnt_acc degrees 0.2 0.2Pointing method. Not Recorded but must meet Pointing Error automatic automatic automatic

Link 4 With 100mm/hr rain on Link 4 With Clear Sky on Link 4Frequency. C.1.a s_beam freq_max GHz 12.75 12.75

C.1.b s_beam freq_min GHz 10.95 10.95

G/T or T. C.10.d.6 e_as_stn noise_tK including, sky, moisture, cloud at 10 degrees elevation

318 157

Antenna diameter B.5.a e_ant gain m 13.0m 6Typical antenna efficiency. B.5.a e_ant gain % 60 55

C.10.d.3 e_as_stn gain dBi 62 54.9Antenna patterns. B.5.b e_ant bmwdth degrees 0.13 0.3

B.5.c e_ant attch_e dBi at +/-2.5degrees 12.9 15.9Pointing error. B.3.d s_beam pnt_acc degrees 0.03 0.07Pointing method. Not Recorded but must meet Pointing Error tracking tracking tracking


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30/20 GHz general and space station characteristicsGeneral CNPC Link Parameters AP 4 Data Item Name from Preface Units System 1 Proposed Maximum Value Proposed Typical Value

Telecommand, UACS-to-space station-to-UA (Link 1 and 2)Information data rate C.9.a.4.a mod_char bit_rate kbps 5000 25 10Modulation Type. C.9.a.4.b mod_char nbr_phase 2 2 2FEC Type. User Dependent and Not Recorded 1/2 1/3 1/3Spectral efficiency. User Dependent and Not Recorded 0.25 0.25 0.25Eb/No @ 1E-8 BER. User Dependent and Not Recorded dB 4 4Roll-off factor. User Dependent and Not Recorded % 20 35 35Reference bandwidths. User Dependent and Not Recorded kHz 100 40Protection Ratio - Intra System C.12.a s_beam prot_ratio I/N dB -6 -6Protection Ratio - Inter System C.12.a s_beam prot_ratio I/N dB -9 -9

Telemetry, UA-to-space station-to-UACS (Link 3 and 4)Information data rate C.9.a.4.a mod_char bit_rate kbps 5000 300 70Modulation Type. C.9.a.4.b mod_char nbr_phase 2 2 2FEC Type. User Dependent and Not Recorded 1/2 1/3 1/3Spectral efficiency. User Dependent and Not Recorded 0.25 0.25 0.25Eb/No @ 1E-8 BER. User Dependent and Not Recorded dB 4 4dBRoll-off factor. User Dependent and Not Recorded % 20 35 35Reference bandwidths. User Dependent and Not Recorded kHz 1200 280Protection Ratio - Intra System C.12.a s_beam prot_ratio I/N dB -6 -6Protection Ratio - Inter System C.12.a s_beam prot_ratio I/N dB -9 -9

Space Station Characteristics. Transmission Link 2 and 4. Reception Link 1 and 3.Transmission Characteristics for each Link (2 and 4)

Frequency. C.1.a s_beam freq_max GHz 20.2 20.2 20.2C.1.b s_beam freq_min GHz 19.7 19.7 19.7

3 dB beamwidth. B.3.a.1 s_beam gain degrees 0.7 1.5e.i.r.p. transmit density. Derived from Maximum transmit power and aggregate bandwidth dBW/1MHz at EOC 45 (Link2) 25.8 (Link4) 41 35

C.8.d.1 grp pwr_max dBW 1.1 (Link2) 0.0 (Link4) 50 48C.8.d.2 grp bdwdth_aggr MHz 36 36B.3.a.1 s_beam gain dBi at EOC 35 31

Link 2 power flux-density. Calculated from e.i.r.p. transmit density and link budget dB(W/m2) in 1MHz -131.1 -115Link 4 power flux density. Calculated from e.i.r.p. transmit density and link budget dB(W/m2) in 1MHz -125.9 -131

Reception Characteristics for each Link (1 and 3)Frequency. C.1.a s_beam freq_max GHz 30 30 30

C.1.b s_beam freq_min GHz 29.5 29.5 29.53 dB beamwidth. B.3.a.1 s_beam gain degrees 0.7 1.5

B.3.a.1 s_beam gain dBi at EOCG/T or T C.5.a grp noise_t dBi/K at EOC 17.9 14 8


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30/20 GHz links 1, 2, 3 and 4 characteristicsUACS Earth Station Characteristics (Link 1 and 4) and UA Earth Station Characteristics (Link 3 and 2)

Transmission Characteristic for each Link (1 and 3) AP 4 Data Item Name from Preface Proposed Maximum Value Proposed Typical ValueLink 1 With Clear Sky on Link 1 With 100mm/hr rain on Link 1 With Clear Sky on Link 1

Frequency. C.1.a s_beam freq_max GHz 28.6 30 30C.1.b s_beam freq_min GHz 27.5 29.5 29.5

Maximum on-axis e.i.r.p. density. Derived from Maximum transmit power, aggregate bandwidth and antenna gain dB(W/40kHz) 67.7dB/6000 67.6/40 52.5/40C.8.g.1 grp pwr_max dBW 1.2dBW -10.4C.8.g.2 grp bdwdth_aggr kHz 6000 100 40C.10.d.3 e_as_stn gain dBi 60.2 70 62.9

Maximum off-axis e.i.r.p density. Derived from Maximum on-axis e.i.r.p. density and Antenna Pattern dB(W/40kHz) at +/- 2.5degrees 8.5dB(W/40kHz) at +/- 2.5degrees 3.9dB(W/40kHz) at +/- 2.5degreesAntenna diameter B.5.a e_ant gain m 4.8 13 6Typical antenna efficiency. B.5.a e_ant gain % 60 60 55Antenna pattern. B.5.b e_ant bmwdth degrees 0.156 0.05 0.12

B.5.c e_ant attch_e dBi at +/-2.5degrees 10.9 14.3Pointing error. B.3.d s_beam pnt_acc degrees 0.5dBi 0.01 0.03Pointing method. Not Recorded but must meet Pointing Error tracking tracking tracking trackingPower control. C.8.i emiss pwr_ctrl automatic automatic automatic automatic

Link 3 UA above rain height UA above rain height UA above rain heightFrequency. C.1.a s_beam freq_max GHz 30 30 30

C.1.b s_beam freq_min GHz 27.5 29.5 29.5Maximum on-axis e.i.r.p. density. Derived from Maximum transmit power, aggregate bandwidth and antenna gain dB(W/40kHz) 26.3 40.8 35.4

C.8.g.1 grp pwr_max dBW 10 6.6 -1.1C.8.g.2 grp bdwdth_aggr kHz 6400 1200 280C.10.d.3 e_as_stn gain dBi 38.3 48.9 45

Maximum off-axis e.i.r.p density. Derived from Maximum on-axis e.i.r.p. density and Antenna Pattern dB(W/40kHz) at +/- 2.5degrees 16 8.5 8.8Antenna diameter B.5.a e_ant gain m 0.65 1.2 0.8Typical antenna efficiency. B.5.a e_ant gain % 45 55 50Antenna pattern. B.5.b e_ant bmwdth degrees 0.9 0.6 0.9

B.5.c e_ant attch_e dBi at +/-2.5degrees 28 16.6 18.4Pointing error. B.3.d s_beam pnt_acc degrees 0.2 0.2 0.2Pointing method. Not Recorded but must meet Pointing Error automatic automatic automatic automaticPower control. C.8.i emiss pwr_ctrl none none none none

Reception Characteristics for each Link (2 and 4)Link 2 UA above rain height UA above rain height UA above rain height

Frequency. C.1.a s_beam freq_max GHz 20.2 20.2 20.2C.1.b s_beam freq_min GHz 17.3 19.7 19.7

G/T or T. C.10.d.6 e_as_stn noise_t K including, sky, moisture, cloud at 10 degrees elevation

12.2 @ 45 238 238

Antenna diameter B.5.a e_ant gain m 0.65 (horizontal axis) 1.2 0.8Typical antenna efficiency. B.5.a e_ant gain % 50 50 50

C.10.d.3 e_as_stn gain dBi 35.2 45.4 41.5Antenna patterns. B.5.b e_ant bmwdth degrees 1.3 0.9 1.3

B.5.c e_ant attch_e dBi at +/-2.5degrees 24.7 13.2 14.6Pointing error. B.3.d s_beam pnt_acc degrees 0.2 0.2 0.2Pointing method. Not Recorded but must meet Pointing Error automatic automatic automatic automatic

Link 4 With Clear Sky on Link 4 With 100mm/hr rain on Link 4 With Clear Sky on Link 4Frequency. C.1.a s_beam freq_max GHz 18.8 20.2 20.2

C.1.b s_beam freq_min GHz 17.7 19.7 19.7

G/T or T. C.10.d.6 e_as_stn noise_tK including, sky, moisture, cloud at 10 degrees elevation 32.4

331 209

Antenna diameter B.5.a e_ant gain m 4.8 13 6Typical antenna efficiency. B.5.a e_ant gain % 60 60 55

C.10.d.3 e_as_stn gain dBi 56.5 66.5 59.4Antenna patterns. B.5.b e_ant bmwdth degrees 0.24 0.08 0.18

B.5.c e_ant attch_e dBi at +/-2.5degrees 8 10.9Pointing error. B.3.d s_beam pnt_acc degrees 0.5dB 0.02 0.05Pointing method. Not Recorded but must meet Pointing Error tracking tracking tracking tracking


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ANNEXTTACHMENT 2A

On-board Unmanned Aircraft Tracking Antenna Development

for Satellite Communication

1 Introduction

1.1 Background

Unmanned aircraft systems (UAS) have been attracting attention in recent years in the world for a variety of applications such as supervision and monitoring of wind and flood damages. The realization of the control and non-payload communication (CNPC) links for the operation of UAS between a remote pilot and unmanned aircraft (UA) in the beyond-line-of-sight (BLOS) areas enables the flight in a wide range by the use of the functions of the global scale of fixed satellite service (FSS) network. Since the Ku/Ka bands are already crowded, we need to consider sharing the bands with those of existing systems such as FSS and also the interference from/to the other satellites. For these reasons, the research and development of interference mitigation techniques has become an urgent issue. Specifically, the antenna beam of on-board tracking antenna must be appropriately controlled to prevent adverse effects on the other satellites.

In Japan, several government-commissioned research projects of the Ministry of Internal Affairs and Communications have been conducted for realizing new wireless communication applications using UAS [1]. This document presents the development of an on-board Ka-band tracking antenna in order to meet the needs of the implementation of the UAS CNPC links between the UA and satellite as an example of the government-commissioned research projects.

1.22 UAS CNPC link

Figure 1 illustrates UAS using satellite links considered in ITU-R, which consists of a geostationary satellite station for FSS, an unmanned aircraft earth station (UAES) and an unmanned aircraft control station (UACS). In this system, we consider that the CNPC links, which are performed between UACS and UAES, are divided into Links 1, 2, 3, and 4 as shown in Fig. 1.

The characteristics of the links 1 and 4 between UACS and FSS space station (FSS-SS) in Fig. 1 can be considered to be equated with those of the conventional satellite communication channel. However, the characteristics of the links 2 and 3 between FSS-SS and UAES may be different from those of the links 1 and 4. When we develop on-board antenna for UA, we have to take into account the characteristics of the propagation of the links 2 and 3 and the motion characteristics of the UA. It is also necessary to refer relevant standards such as the protection criterions for UAS and for existing systems.


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FIGURE 1

Unmanned aircraft system and CNPC links

23 Performance requirements considering the use of UAS

23.1 Design principles of the Ka-band radiation unit

As the first step toward development to on-board antenna for UA, the characteristics of the propagation of the links between satellite and UAES and the motion characteristics of the UA are taken into account. It is also needed to refer to relevant standards such as protection criteria of existing systems and UAS. There are several discussions to be referred on the relevant CNPC links to operate UAS such as the working document towards a new Report ITU-R M.[UAS-FSS] in ITU-R. On the other hand, there is another discussion on the use of Earth Stations In Motion (ESIMs) which operates in Ka-band GSO FSS networks (RR No. 5.527A and Res. 156 (WRC-15)).

In consideration of the above factors, a Ka-band on-board antenna for the UAS was developed to meet the following conditions:– Consider the angle ranges of the antenna tracking by considering the longitude and

latitude from Japan to track the stationary satellites, and control of the antenna beam.– Whenever possible, to reduce the size, weight, power saving.– Consider lowering the height of the antenna mounting system.– Consider the flexible mounting performance in order to respond to diversification of

mobile communication using geostationary satellites.– Wide bandwidth to satisfy the ESIMs of the Ka band (29.5 ~ 30.0 GHz/

19.7 ~ 20.2 GHz band)– Off-axis e.i.r.p. satisfies Recommendation ITU-R S.524-9.

Most Ku/Ka-band on-board antennas under development or existing have multi-horns or slot array as feeding method to make beam formation. As for the antenna beam control system, they mostly introduce mechanical drive system. Generally, phased array system is advantageous to control the angle of the flexible beam forming. Also, it is possible to reduce the height of the rotation diameter of the antenna.


5 GHz bandKu/Ka band

5 GHz band

Remote PilotUnmanned Aircraft Control Station (UACS)Earth Station

UA Earth Station(UAES)

UAS CNPC Links1+2: Forward link (Remote

pilot to UA)1: Forward uplink (E-s)2: Forward downlink (s-E)3+4: Return link (UA to remote

pilot)3: Return uplink (E-s)4: Return downlink (s-E)

Fix Satellite Station (FSS) Space Station

4

31

2

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Meanwhile, there are some drawbacks of the phased array antenna such as a decrease in gain as a decrease in the effective aperture plane, the high power consumption, and high cost. Referring to the development or some existing Ku/Ka-band onboard antennas, the reason why they introduced a mechanical drive system to the altitude and azimuth control was understandable.

In view of the currently available technologies, the mechanical drive system of elevation and azimuth control is thought to be a possible solution for on-board UA antennas at this point.

23.2 Required specifications and link budget design

In order to design the antenna specifications for developing the antenna, the communication speed per one UA is supposed to be 5 Mbits/s because of transmitting high quality video images for see-and-avoid in addition to command and control (C2) link, and the communication requirement and conditions for the link budget are summarized in Tables 1 and 2.

As the reference satellite, a broadband communication satellite system ‘WINDS’ developed as an experimental communication satellite to demonstrate technology for broadband satellite communications with Internet Protocol (IP) [2] is assumed

TABLE 1

Antenna specifications requirement

No. Items Values Comments1 G/T Over 10.0 dB/K @18.9 GHz Information speed: 5 Mbits/s

Margin: 1.5 dB

2 e.i.r.p. Over 46.7 dBW @28.6 GHz Information speed: 5 Mbits/sMargin: 0.8 dB

3 e.i.r.p. density 24.5 dBW/40kHz @28.6 GHz Information speed: 5 Mbits/sSymbol rate: 6.02 Msymbols/s

4 BUC output 10 W

TABLE 2

Assumed conditions for link budget

No. Items Values Comments1 Satellite G/T 17.7 dB/K WINDS satellite[2]

2 Repeater Vent pipe

3 Frequency Tx: 28.6 GHzRx: 18.9 GHz

4 Earth station SDR-VSAT with 2.4 m antenna

5 Modem IDirect Infinity@5000

6 Rain attenuation None

7 Modulation method QPSK, FEC rage: 0.495, C/N: 4.0 dB, Occupied bandwidth: 6.02 MHz

Information speed rate: 5 Mbits/s


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34 Development of unmanned aircraft tracking antenna system Ka-band Radiation Unit

34.1 Design of radiation unitResults of Antenna Design

As the results of the above discussion, a Cassegrain type antenna system with elliptical aperture reflector is introduced since it is able to expect a lower weight and manufacturing costs while reducing the height of the antenna. The Cassegrain system with elliptical aperture reflector also offers a wide frequency band to support the allocated ESIMs frequency Ka-band.

The hybrid analysis of physical optics approximation and the finite element method (FEM) was utilized to design and analyze the radiation unit. Moreover, the reflector shaping technique [3] that takes into account the suppression of scattered waves such as diffracted waves was utilized to achieve low profile and to satisfy the low side-lobe defined by ITU-R S.524-9.

Figure 2 shows the result of the appearance of the radiation unit with two reflectors. As shown in Fig. 2, the radiation unit is composed of the main reflector, the sub-reflector, the primary radiator and the cone. The shape of the main reflector is close to elliptical because of the low profile. As the result of the antenna design, the antenna gains of the antenna achieve more than 35.3 dBi and 38.3 dBi at 18.9 GHz and 27.5 GHz, respectively. Table 3 summarizes the result of the antenna design.

FIGURE 2

Appearance of the radiation unit.

TABLE 3

Summarizes the results of the antenna design.

No. Items Values Comments1 Tx Frequency 27.5-30.0 GHz2 Rx Frequency 17.3-20.2 GHz

3 Off-axis e.i.r.p. ITU-R S.524-924.5dBW/40kHz

4 Size Height < 22.2 cm Without radome5 Polarization Tx: right-handed circularly

Rx: left-handed circularly6 G/T Over 10.0dB/[email protected]

7 e.i.r.p. Over 46.8dBW


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34.2 Evaluation of Radiation Unit of On-Board Antenna

Several characteristics of the developed radiation unit were evaluated. The measured receive G/T values are listed in Table 34 and the off-axis radiation patterns obtained in a compact range anechoic chamber are shown in Fig. 3. As shown in the results, the developed radiation unit of the on-board antenna satisfied the antenna requirements defined in Recommendation ITU-R S.524-9 and system parameters to realize 5 Mbits/s communication speed. The 2-D radiation patterns using a near field measurement system were also measured. From these results, the symmetries of the antenna patterns were also confirmed.

TABLE 34

Measured receive G/T valuesFrequency Unit 17.7

GHz18.3 GHz

18.9 GHz

19.2 GHz

20.2 GHz

Gain dBi 34.0 34.7 35.2 35.7 35.8System Noise Temp dB 22.5 22.5 23.0 22.3 22.6

K 174.8 176.7 197.5 167.3 179.0Antenna noise temp K 86.1 78.3 106.4 74.2 85.9

LNA noise temp K 88.7 98.4 93.1 93.1 93.1G/T dB/K 11.5 12.2 12.2 13.4 13.2

FIGURE 3

Measured off-axis radiation pattern-1 and pattern-2 around 0 degrees

5 Development of On-board Tracking Antenna System

35.31 Design of tracking antenna unit

In view of the design target values, a variable directional antenna driving control unit was designed to satisfy the requirement of the on-board antenna for UAS. The block diagram of on-board unmanned aircraft tracking antenna including the developed radiation unit and the antenna driving unit is shown in Fig. 4. The on-board unmanned aircraft tracking antenna consists of a radiation unit, low noise block down converter (LNB), a transmit block up converter (BUC), actuator & control unit, and so on.


ITU-R S.524-9

ITU-R S.524-9

https://www.itu.int/rec/R-REC-S.524-9-200604-I/en

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As for the driving range, the azimuth (AZ) range is designed to cover continuous 360 degrees, and the elevation (EL) range is 0 to 90 degrees. The several design target values of the antenna tracking unit are summarized in Table 5.

As the result of the development of the on-board antenna, Figure 5 shows the appearance view and configuration of the antenna unit.

FIGURE 4

Block diagram of on-board unmanned aircraft tracking antenna


LNB

NW HUB

AC 100VIRUMODEM

ACU

MotorEL

MotorAZ

S/RAZ

ComponentControlR/JEL

R/JAZ

BUC

FEED

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FIGURE 5

Appearance view and configuration of on-board unmanned aircraft tracking antenna

TABLE 5

Design target values of the antenna tracking unit

Drive range AZ: 360 degrees (continual move)EL: 0 to 90 degrees

Drive speed AZ: > 40 degrees/sEL: > 25 degrees/s

Angular accuracy < 0.2 degrees

Antenna unit height < 30 cm

Total antenna unit weight < 30 kg

35.42 Evaluation of the antenna tracking unit

Several performance evaluations of the antenna tracking unit were conducted such as tracking error to confirm several characteristics of the antenna tracking system. As a result of the evaluation, an example of the results, Figures 6 and 7 show the tracking responses of AZ and EL axes when the AZ and EL target angles are changed from zero degrees to 10 degrees. As shown in these figures, the tracking errors of both AZ and EL axes meets within 0.2 degrees including over-shoots.


AZ motor

EL motor

BUC

Radiation Unit

Control Unit

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Table 6 summarizes some results of the antenna performance.

FIGURE 6

Step response of AZ tracking.

FIGURE 7

Step response of EL tracking.

3.5 Characteristics of the unmanned aircraft tracking antenna system

Table 4 summarizes the characteristics of the developed Ka-band Unmanned Aircraft Tracking Antenna System particularly in regards to link 2 and 3.


Time [s]

Time [s]

AZ target values [deg]AZ measured values [deg]

EL target values [deg]EL measured values [deg]

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TABLE 46

Some characteristics of the Ka-band on-board antenna results of the antenna performance

Reception Characteristics for Link 2

Items Values CommentsFrequency Max 20.20 GHz

Min 17.30 GHzG/T 12.2 dB/K @ 18.9 GHz Including, sky,

moisture, cloud at 45 degrees elevation

Antenna diameter Gain 0.65 m horizontal axis

Typical antenna efficiency 50 %35.2 dBi @ 18.9 GHz

Antenna patterns Beam width 1.3 degrees24.7dBi at +/-2.5degrees

Pointing error < 0.184 degreePointing method automatic

Transmission Characteristic for Link 3Frequency Max 30.00 GHz

Min 27.50 GHzMaximum on-axis e.i.r.p. density.

26.3 dB(W/40kHz)

Power_max 10.0 dBW

Bandwidth_aggr 6 400 kHzGain 38.3 dBi

Maximum off-axis e.i.r.p density.

16 dB(W/40kHz) at +/- 2.5 degrees

Antenna diameter 0.65 mTypical antenna efficiency. 45 %

Antenna pattern. 0.9 degrees28 dBi at +/-2.5degrees

Pointing error < 0.184 degreePointing method. automatic

Power control. noneOther characteristics

Antenna size Height < 26 cm Without radomeTotal weight 28.8 kg

Polarization Tx: right-handed circularlyRx: left-handed circularly

AZ, EZ angle range AZ: 360 degrees (continual move)EL: -10 to 90 degrees

AZ, EZ angle speed AZ: 80 degrees/s


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EL: 140 degrees/s


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No. Items Values Comments1 Tx Frequency 28.172 to 29 GHz2 Rx Frequency 18.372 to 19.3 GHz

3 Off-axis e.i.r.p. < 24.5 dBW/40 kHz ITU-R S.524-94 Size Height < 26 cm Without radome

5 Total weight 28.8 kg6 Polarization Tx: right-handed circularly

Rx: left-handed circularly7 G/T Over 12.2 dB/K @18.9GHz

8 e.i.r.p. Over 46.5 dBW9 AZ, EZ angle

rangleAZ: 360 degrees (continual move)EL: -10 to 90 degrees

10 AZ, EZ angle speed

AZ: 80 degrees/sEL: 140 degrees/s

11 Tracking error < 0.184 degree

46 Evaluation test using an actual aircraftThe total performance of the developed on-board antenna was evaluated using a small manned airplane by communicating with the experimental communication satellite ‘WINDS’ for broadband satellite communications with Internet Protocol (IP) in the 20/30 GHz band. Appendix A summarizes some information of the WINDS satellite. Figure 68 shows the aircraft and mounted antenna used for the evaluation campaign. As shown in Fig. 68, the cCommunications to the back of the aircraft cannot be performed due to the mounting condition of the aircraft and there is a gain attenuation by the head of the pilot in the specified angle range.

Figure 79 shows the received C/N, the altitude and the azimuth of the aircraft, and the antenna transmission control signal (inter-lock signal) output which indicates the cases of the decrease in the reception level and excessive tolerance of the tracking error (± 0.2 degrees or more) obtained by the test that reached a stable altitude (2000 m) from the takeoff of the aircraft and lowered altitude while turning. The horizontal axis indicatesis time (second).

From this result, almost the theoretical C/N values can be received when the directivity of the antenna is within the receivable range, and the communication control can be performed properly when the reception level is lowered or the tracking error exceeds the allowable range.


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FIGURE 68

Appearance of airplane and on-board antenna

FIGURE 79

An example of measurement result of the evaluation test

57 ConclusionThis document provides the background of a new communication system which utilized the frequency band of the fixed-satellite service for the command and non-payload communication links for the operation of unmanned aircraft systems and mentioned the results of the developing of the on-board Ka band tracking antenna for unmanned aircraft system.


Pilot head

Communication coverage On-board antenna

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References[1] Miura, R., Inoue, M., Owada Y., Takizawa, K., Ono, F., Suzuki, M., Tsuji, H., and

Hamaguchi, K., “Disaster-resilient wireless mesh network,” Proc. WPMC2013, Atlantic City, USA, June 27, 2013.

[2] Kadowaki, N., Yoshimura, N., Ogawa, Y., Hashimoto, Y., “High Performance On-Board Switch for The Next Generation Multi-Beam Satellite,” Proceedings of IAC 2004, Vancouver, Canada, Oct. 4-8, 2004.

[3] Inasawa, Y., “Design Method for A Low-Profile Dual-Shaped Reflector Antenna with An Elliptical Aperture by The Suppression of Undesired Scattering,” IEICE Trans., 91-C, April 2008, pp.615-624.


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APPENDIX A

Wideband InterNetworking engineering test and Demonstration Satellite (WINDS)

The Wideband InterNetworking engineering test and Demonstration Satellite (WINDS) was developed for establishing high-speed satellite communications technologies. WINDS was launched on February 23, 2008 and is a geostationary satellite located at 143 degrees of east longitude. It uses the Ka-band (28 GHz uplink / 18 GHz downlink) for communication. The details of WINDS information can be obtained as identification number ‘108501175’ as ‘WINDS-A’ satellite network name in ITU-R.

Figure 1 shows a block diagram of the WINDS communication transponder. One of the WINDS major characteristics of the satellite is its onboard switch called ATM Baseband Switch (ABS), which demodulates the signal from antenna, switches the data based on the cell, modulates the signal, and sends the signal to the antenna. The communication mode using ABS is called “regenerative mode”, while the communication mode using a band pass filter (BPF) bypassing the ABS is called “bent-pipe mode”. In the regenerative mode, the uplink data rate is selected from 1.5 Mbps, 6 Mbps, 24 Mbps, 51 Mpbs, or 155 Mbps, with a downlink data rate of 155 Mpbs. In the bent-pipe mode, the communication link can be used up to 1.1 GHz bandwidth, with the communication data rate up to 1.2 Gbps.

As shown in Fig. 2, the satellite has two antenna systems. One is a fixed beam, with multiple sub-beams, antenna and a multi-port amplifier; another is a steerable beam antenna with an active phased array system. One sub-beam of the fixed beams covers Japan and Beijing, Seoul, and Shanghai, and the other covers seven southeast Asian cities including Hong Kong, Singapore, and Bangkok. On the other hand, the steerable beam antenna has two receiving beams (RX beam) and two transmitting beams (TX beam), which has a service coverage over the Asian and Pacific countries.


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FIGURE 1

Block diagram of WINDS transponder

FIGURE 2

Service areas of the broadband communication satellite

______________


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