artemis announcement of opportunity - esa artes a0 - issue 1.0.pdf · reference documentation ......

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ESA-TIA-T-AO-0001

Date: 19 December 2012 Issue 1 Rev 0

ESA UNCLASSIFIED – Releasable to the Public

ARTEMIS Announcement of Opportunity

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Title ARTEMIS Announcement of Opportunity

Issue 1 Revision 0

Author TIA-TFS 19 December 2012

Reason for change Issue Revision Date

Issue Revision

Reason for change Date Pages Paragraph(s)

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Table of contents:

1 ACRONYMS ................................................................................................................................................................ 5 2 REFERENCE DOCUMENTATION ......................................................................................................................... 8 3 BACKGROUND .......................................................................................................................................................... 8 4 INTRODUCTION ....................................................................................................................................................... 9 5 DESCRIPTION OF THE OPPORTUNITY ............................................................................................................. 9

5.1 MAIN PRINCIPLES OF THE OPPORTUNITY .................................................................................................................. 9 5.2 ARTEMIS MISSION DESCRIPTION ............................................................................................................................ 9

5.2.1 SILEX mission ................................................................................................................................................. 10 5.2.2 SK Data Relay mission ................................................................................................................................... 10 5.2.3 Navigation mission ......................................................................................................................................... 11 5.2.4 LLM Mission ................................................................................................................................................... 12

5.3 ARTEMIS ITU FILINGS ......................................................................................................................................... 12 6 CONDITIONS OF THE ESA ARTEMIS ANNOUNCEMENT OF OPPORTUNITY ...................................... 14

6.1 TRANSFER OF OWNERSHIP OF ARTEMIS ASSET .................................................................................................... 14 6.2 TRANSFER OF RIGHTS AND OBLIGATION OF THE CORRESPONDING ITU FILINGS .................................................... 14 6.3 ARTEMIS OPERATION .......................................................................................................................................... 14 6.4 ARTEMIS DE-ORBITING ........................................................................................................................................ 15 6.5 EXPECTED BENEFIT FOR ESA FROM THIS AO ........................................................................................................ 15 6.6 CONTRACTUAL CONDITIONS .................................................................................................................................. 16

7 SELECTION PROCEDURE AND EVALUATION CRITERIA ......................................................................... 18 7.1 SELECTION PROCEDURE ......................................................................................................................................... 18

7.1.1 Step 1: Notice of Intent ................................................................................................................................... 18 7.1.2 Step 2: Dialogue phase ................................................................................................................................... 18 7.1.3 Step 3: Proposal submission ........................................................................................................................... 19 7.1.4 Step 4: Final selection .................................................................................................................................... 19

7.2 AO PROCESS SCHEDULE ......................................................................................................................................... 19 7.3 EVALUATION CRITERIA .......................................................................................................................................... 19

8 PROPOSAL GUIDELINES ...................................................................................................................................... 20 8.1 GENERAL TENDER CONDITIONS .............................................................................................................................. 20 8.2 PROPOSAL CONTENT .............................................................................................................................................. 20

APPENDIX A NOTICE OF INTENT FORM ........................................................................................................... 22 APPENDIX B ARTEMIS TECHNICAL DESCRIPTION ...................................................................................... 23

SATELLITE ....................................................................................................................................................................... 23 SILEX (Semiconductor Intersatellite Link Experiment) payload ............................................................................... 26 SKDR Payload (S/Ka-band Data Relay) ..................................................................................................................... 26 NAV Payload ............................................................................................................................................................... 27 LLM Payload ............................................................................................................................................................... 28

GROUND SEGMENT .......................................................................................................................................................... 28 APPENDIX C ARTEMIS OPERATIONS DESCRIPTION .................................................................................... 29

ARTEMIS SATELLITE CONTROL CENTRE (FUCINO) ....................................................................................................... 29 ARTEMIS MISSION CONTROL CENTRE (REDU) ............................................................................................................... 30 USERS INTERFACES .......................................................................................................................................................... 31 ESA EARTH TERMINAL AND IOT FACILITIES (REDU) ...................................................................................................... 31

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APPENDIX D ARTEMIS FILINGS ........................................................................................................................... 53 ARTEMIS-21.5E-DR ..................................................................................................................................................... 53

TT&C links in S-band .................................................................................................................................................. 53 Feeder links and TT&C nominal links in Ka-band ..................................................................................................... 53 Ka-band inter-satellite links for data relay function ................................................................................................... 55 S-band intersatellite links for data relay functions ..................................................................................................... 56

ARTEMIS-21.5E-LM ..................................................................................................................................................... 56 Feeder links ................................................................................................................................................................. 56 L-band user links ......................................................................................................................................................... 57

ARTEMIS-21.5E-NAV .................................................................................................................................................. 57 Feeder links ................................................................................................................................................................. 57 Users link ..................................................................................................................................................................... 57

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1 ACRONYMS

AMCF ARTEMIS Mission Control Facility AO Announcement of Opportunity. AOCC ARTEMIS Operations Control Centre ARTEMIS Advanced Data Relay and Technology Mission ASCII American Standard Code for Information Interchange ATV Automated Transfer Vehicle AVP ARTEMIS Availability Plan BAFO Best and Final Offer CMS Control and Monitoring System CET Central Earth Terminal CNES Centre National d'Etudes Spatiales COS Combined Operations Schedule DAP ARTEMIS Detailed Assignment Plan DRS Data Relay Satellite DRTM Data Relay and Technology Mission DSR Detailed Service Request DTS Detailed Telecommand Schedule EC European Commission EGNOS European Geostationary Navigation Overlay Service ESRIN European Space Research Institute ESSP Earth System Science Partnership FD Flight Dynamics FES Fixed Earth Station GEO Geostationary Earth Orbit GHz GigaHertz GTO Geosyncronous Transfer Orbit HEX Hexadecimal ICD Interface Control Document ICS Interface de Communication Standard IOL Inter-Orbit Link IOT In-Orbit Test IOTE In-Orbit Test and Experimentation IP Inter-Pass ISS International Space Station ITU International Telecommunication Union JAXA Japan Aerospace Exploration Agency LEO Low Earth Orbit LLM L band Land Mobile MIB MCF Information Base MP Master Plan MPS Mission Planning System MUT Mobile User Terminal MVM Microvibration Monitor

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OBT On-Board Time ODR Optical Data Relay OGS Optical Ground Station OPALE Optical Payload for ARTEMIS Link Experiment (GEO Passenger) ORB Orbit Prediction Messages ORM Operators Review Meeting OSM Operations Status/Scheduling Message OUP Outline Utilisation Plan PFOS Platform Operations Schedule PLOS Payload Operations Schedule PO Programme Office PTL Payload Test Laboratory SCC Satellite Control Center SDM Service Data Message SILEX Semiconductor Laser Inter-orbit Link Experiment SIR Service Incident Report SKDR S-Band/Ka-Band Data Relay SLA Service Level Agreement SR Elementary Services Request STDM Spacecraft Trajectory Data Message TBC To Be Confirmed TBD To Be Defined TC Telecommand TDRSS Tracking and Data Relay Satellite System TM Telemetry TMS Test and Monitoring Stations TTC Telemetry, Tracking and Command UCI User Communication Interface UCO User Coordination Offices UET User Earth Terminal USCC User Spacecraft Control Centre USC User Spacecraft USP User Service Profile UST User Space Terminal USV Unmanned Space Vehicle UTC Universal Time Coordinated

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2 REFERENCE DOCUMENTATION

No reference documentation

3 BACKGROUND

ARTEMIS has successfully completed more than 10 years in orbit, since its launch in July 2001. All the on-board payloads have operated with level of performances that exceeded the initial design goals. Some of the technologies on board, and in particular the electric propulsion, have also proved fundamental to rescue the satellite after the launch failure and to allow the completion of the mission. Since July 2011, the ARTEMIS mission has been extended beyond its design lifetime on a “best effort” basis in the attempt to satisfy the operational needs of the users until March 2013. A mission completion plan has been presented to ESA Council including the plan for the ramp down of operations, the de-orbiting of the Satellite and the end of the programme. Before proceeding to the execution of the mission completion plan, ESA issues this Announcement of Opportunity aimed at European Satellite Operators for taking full ownership of the ARTEMIS satellite, assuming full liability for the operations of the satellite as well as benefiting from the rights and obligations of the corresponding satellite ITU frequency filings.

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4 INTRODUCTION

This document presents the ESA ARTEMIS Announcement of Opportunity including: • Description of the opportunity • Conditions of the ESA ARTEMIS Announcement of Opportunity • Selection process • Evaluation Criteria • Proposal guidelines

Four annexes provide the Bidders information regarding: • Appendix A: Template for Notice of intent. • Appendix B: ARTEMIS Technical description • Appendix C: ARTEMIS Operation description • Appendix D: ARTEMIS frequency filings

5 DESCRIPTION OF THE OPPORTUNITY

5.1 Main principles of the opportunity

This Announcement provides an opportunity for a European Operator to obtain the full ownership of the ARTEMIS satellite as well as the rights and obligations associated to the corresponding ITU frequency filing. In return the Operator shall offer a concrete plan that will support/generate activities benefiting the European Space Telecom Industry. These activities do not have to be directly related to the exploitation of the ARTEMIS satellite. It is therefore left to the Bidding Operators to define and propose the nature of these activities. The Operator shall also become solely responsible for the operations and the de-orbiting of the ARTEMIS satellite at its end of life. The Operator shall assume full responsibility for liabilities arising from the operation of ARTEMIS. This Announcement describes the conditions for the transfer (in section 6) and the selection process for the Operator (in section 7). The final decision on the transfer of ownership of the ARTEMIS satellite is subject to ESA Council agreement.

5.2 ARTEMIS mission description

The long list of ARTEMIS mission achievements starts on 12 July 2001, after the separation from Ariane 5 in an orbit that was half way from the target GTO. Since then, ARTEMIS has managed to claim an outstanding number of world premières and mission goals. The orbit recovery was realised through the combination of the first major reprogramming of a telecommunications satellite in orbit and the first orbital transfer to geostationary orbit using electrical propulsion.

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The ARTEMIS satellite design lifetime was 10 years and the mission has been declared completed on April 2012. Since then ARTEMIS is operated on the best effort basis under request of its institutional users.

5.2.1 SILEX mission

The ARTEMIS part of the Silex, the OPALE, has performed well during the entire mission. In conjunction with its LEO counterpart embarked on SPOT-4, the first optical inter-satellite link was performed in December 2001, while ARTEMIS was still en-route to its final GEO slot. The optical inter-satellite link with SPOT-4 was operated at the rate of 1 session per day, until January 2008, when the service had to be suspended due to an unrecoverable failure on the PASTEL terminal on-board SPOT-4. In total 1789 communication sessions were successfully completed for a total of 378 cumulated hours of transmissions with a success rate in excess of 96%. The OPALE terminal has also been successfully utilised for experimental data transmission with the JAXA satellite Kirari. The experimental phase lasted 12 months, between December 2005 and 2006. During this period 108 optical links were successfully completed for an overall duration of 24 hours and a success rate above 98%. The optical terminal embarked on Kirari had been developed by JAXA on the base of ICD information exchanged between the two agencies. More results in the optical data relay domain were realised between 2006 and 2007 when ARTEMIS established successful bi-directional links with an airplane flying over the southern coast of France with a remarkable reliability. During the mission, the OPALE terminal has also been used for experiments with Optical ground Stations in Tenerife and in Kiev. These latter tests confirmed that the terminal is still in good health.

5.2.2 SK Data Relay mission

5.2.2.1 Ka-band mission

The Ka-band mission has progressively grown over the ARTEMIS operational life to become a crucial pillar in the ENVISAT operational set-up. From the first image transferred in June 2003, ENVISAT then utilised 14 to 15 links a day (one 100 Mbit/sec and one 50 Mbit/sec channel) for a total of approximately 7 hours of transmission per day. In total almost 2/3 of the 217 GB of data that ENVISAT sends back to Earth every day was relayed through ARTEMIS. In total, since April 2003, the ENVISAT Ka-band data relay mission has cumulated over 20’240 hours of transmission with a success rate of more than 99%. The Ka-band mission was also successfully tested with the JAXA satellite ADEOS.

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After the end of ENVISAT mission in April 2012, the Ka-band facilities are used only for testing purposes.

5.2.2.2 S-band mission

The S-band mission has been used in an operational scenario in conjunction with the Automated Transfer vehicle (ATV) mission to the International Space Station. The typical service configuration for ATV is two telemetry channels (at 8 and 64 kbps) and one telecommand channel (at 1 kbps) during the various phases of the mission. ARTEMIS S-band data relay service is hot back-up to the TDRSS during the rendez-vous phase and becomes primary service during the docked phase to the ISS. ATV and ENVISAT operations were interleaved and, due to the different geometry of the orbits on ENVISAT and ATV, require an uninterrupted activity of the SKDR tracking antennae on board ARTEMIS. Three full ATV missions were supported (Jules Vernes and Johannes Kepler ) in 2009 and 2011 respectively for an aggregate duration of 11 months. In total over 2000 hours of communications have been completed, with a success rate of 99%. Support to ATV 3 (Edoardo Amaldi) was provided from March till September 2012. Two additional ATV missions (ATV 4 and 5) could also be supported through ARTEMIS respectively in 2013 and 2014 should the selected Bidder choose to include this service into its answer to this AO. In 2007 ARTEMIS also demonstrated successfully bidirectional links in S-band with the Unmanned Space Vehicle (USV), an unmanned drone dropped from an altitude of 21 Km off the eastern coast of Sardinia. For both missions (USV-1 and USV-2) telemetries and telecommands were exchanged with the drone body mounted omnidirectional antennae during the free fall at speeds in excess of Mach 1. Experiments of S-band data relay have also been performed successfully during both JAXA mission, Kirari (OICETS) and ADEOS II.

5.2.3 Navigation mission

The NAV payload has been used in the context of EGNOS space segment based on two GEO satellites in Operation and on one GEO satellite in TEST configuration. From 2003 to 2005 ARTEMIS was used by Industry for system qualification testing, together with Inmarsat’s 3F2 and 3F5. In 2005 ARTEMIS entered the initial operations phase in the TEST configuration, shared between Industry and ESSP for operations qualification and training. At that time Inmarsat 3F2 & 3F5 provided the operational signal.

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In February 2009 ARTEMIS entered the Operational configuration in replacement of Inmarsat-3F5. Since then, it broadcasts 24x7 the EGNOS Signal-in-Space on PRN124. As such the NAV payload has played an essential role for EGNOS to deploy its services:

• October 2009: Open Service declared by EC • March 2nd, 2011: Safety-of-Life Service declared by EC.

EGNOS reconfigured the space segment and utilise ARTEMIS in TEST mode in Q2/2012. In this function the NAV payload is used to achieve the qualification of the EGNOS System release V2.3.2. EGNOS will utilise ARTEMIS until 31/12/2013 should the selected Bidder decide to include this service into its answer to this AO. The NAV payload has operated reliably during the above period with an overall availability figure of 99.92%. The outages were due to the well-known spurious events that randomly affect the ARTEMIS platform services.

5.2.4 LLM Mission

With an L-band mission on-board, ARTEMIS has access to an L-band allocation of 2. 1 MHz obtained through the coordination with the other L-band operators. Telespazio is the largest L-band capacity user on ARTEMIS via a direct contract with ESA. Telespazio uplink their L-band traffic from their Ground Station in Lario (Como, Italy). The LLM services have been continuously available to the Users with the exceptions of a limited number of short outages related to ARTEMIS spurious events that affect the availability of the satellite platform services. The overall service availability figure is 99.89% over the period April 2003-December 2011. The contractual rights and obligations arising from the agreement between ESA and Telespazio will expire at the latest when the selected Operator takes over the full responsibility of ARTEMIS operations. Bidders envisaging to continue with the provision of the L band capacity to Telespazio are invited to negotiate the terms and conditions for such provision directly with Telespazio.

5.3 ARTEMIS ITU filings

The ARTEMIS ITU filing for the orbital position 21.5 E is composed of 3 separate filings: • ARTEMIS-21.5E-DR (AR11/C/2507), covering the Data Relay functions and the

TT&C • ARTEMIS-21.5E-LM (AR11/C/2512), covering the L-band mobile function • ARTEMIS-21.5E-NAV (AR11/C/3688), covering the EGNOS navigation function These filings were generated in the mid-90’s for the Artemis launch in 2001.

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The details of these filings can be found in the ITU database. Appendix D simply summarizes their main characteristics, to allow the Bidders to make a first-level assessment of the potential interest of reusing the filing for a future satellite in the same orbital position. The full details of the ARTEMIS filings can be found in the ITU SNS database. Some bi-lateral coordination agreements further restricted the use of the frequencies indicated in the filing. The details of those constraints will be provided to the Bidders having indicated their interest according to section 7.1.1. The L- band allowed usage (assignment) for ARTEMIS allocation is subject to revision on an annual basis at the Operators Review Meeting (ORM) to reflect the actual and forecasted utilisation needs of the different operators. The current ARTEMIS assignment for 2013 is 1.984 MHz.

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6 CONDITIONS OF THE ESA ARTEMIS ANNOUNCEMENT OF OPPORTUNITY

6.1 Transfer of ownership of ARTEMIS asset

The ownership of the satellite as detailed in Appendix B will be transferred to the selected operator upon approval by the ESA Member States represented in the ESA Council. ESA cannot guarantee the outcome of this process and declines, as a result, any responsibility arising from the pre-contractual stage. The ownership of the ground segment will not be transferred to the selected operator.

6.2 Transfer of rights and obligation of the corresponding ITU filings

The right of use of the frequency filings detailed in section 5.3, which is ancillary to ARTEMIS satellite, will be transferred to the selected Operator. Subject to the approval by the regulatory authorities of the ESA Member States, the selected Operator is responsible for undertaking all the necessary steps with the national administration of his choice in order to register the filing in ITU. The filing for the ARTEMIS satellite is administered by France and it is registered in the name of “FR-ESA”. Given that ESA is not a member of the ITU, the national frequencies authorities of the ESA Member States will be requested to give their consent to amend the filings from ESA to merely one ESA Member State that will become the filing authority for ARTEMIS once the transfer of ownership takes place. The Council will record this consent that will have to be previously communicated by the ESA delegations.

6.3 ARTEMIS operation

Upon the transfer of ownership of the ARTEMIS satellite, the satellite operations are under the responsibility of the selected Operator. The Operator is free to choose the means to undertake this task. Currently, ARTEMIS is operated using the facilities at the Satellite Control Centre and Mission Control Centre in Fucino and Redu respectively. Appendix C describes the ARTEMIS operational set-up. At present, ESA has a contract each with TAS-I (subcontractor Telespazio) and with RSS for the provision of ARTEMIS operations. ESA will organise in February 2013 (on a date to be announced in January 2013) visits both to Fucino and Redu to allow the Bidders (having provided the Notice of Intent) to evaluate the ARTEMIS operational environment. ESA is taking all the necessary steps to close those contracts upon the transfer of ownership of the ARTEMIS satellite. Nevertheless, Bidders may, at their discretion, enter into negotiations with the incumbent contractors in order to continue ARTEMIS operations

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and/or to ensure a smooth transition of the ARTEMIS satellite, to familiarise themselves with the particularities and technical features of the ARTEMIS satellite and its operation as well as to avoid any undesired interruption in the provision of the technical services necessary for operating the ARTEMIS satellite.

6.4 ARTEMIS de-orbiting

The ARTEMIS satellite shall be de-orbited at the end of its usage. Upon the transfer of ownership, ARTEMIS de-orbiting is under the full responsibility of the selected Operator.

6.5 Expected benefit for ESA from this AO

ESA is expecting the Bidder to provide an activity plan that will benefit the European Space Telecom Industry. The nature of these activities is left for the Bidder to define. A list of possible schemes is provided here as examples. This list is only indicative and it is not exhaustive:

• Commitment from the Bidder to support European industry to introduce innovation in their operational environment.

• Commitment for the Utilisation of ARTEMIS satellite for experimental/proof of concept purposes:

o Optical communications space to space / space to ground o UAV link, o Aeronautical Services, o Inter-satellite links, o M2M services, o Interference mitigation, o Etc.

• Committed embarkation and use of identified European innovative Telecom technologies on board future Satellites of the Bidder,

• Committed free of charge satellite real estate for future ESA proposed hosted payload opportunities on board future Satellites of the Bidder,

• Commitment for the re-use (not necessarily related to ARTEMIS operation) of the ARTEMIS ground segment, including ARTEMIS IOT facilities in Ku and Ka-bands, in ESA Redu Centre and/or Fucino.

In addition to this, ESA considers ARTEMIS as the current baseline for the provision of ATV-4 and ATV-5 services. Therefore, the Bidding Operator may decide to provide an offer for the provision of those services. The same principle as explained for the ATV services applies for the provision of EGNOS test services till 31/12/2013. The benefits offered to ESA in exchange for the transfer of ownership do not need to take the form of a monetary compensation. However this is not excluded and such compensation could be considered as part of the benefits for ESA.

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6.6 Contractual conditions

This section highlights the main legal and contractual principles and requirements related to the intended transfer of ownership of the ARTEMIS satellite and the associated regulatory filings, which shall form part of the contract to be concluded between ESA and the selected Operator.

• The operator to be selected as a result of the present AO shall become the owner of the ARTEMIS satellite as described in Appendix B.

• Property and risk of the ARTEMIS satellite shall pass to the selected Operator upon

signature of the contract with ESA resulting from this Announcement of Opportunity. At the same time, possession of the ARTEMIS satellite shall be deemed to have passed to the selected Operator.

• The Agency transfers the ARTEMIS satellite in the condition “as is”; no

representations, warranties or guarantees shall apply to its technical condition, performance or fitness for any particular purpose. The Agency shall not be liable for any latent defects that may emerge post-transfer due to the continued degradation of the technical condition of the ARTEMIS satellite, nor for any direct, indirect, incidental or consequential damage such as but not limited to loss of data, profit, frequency filings and business interruption.

• The selected Operator shall be liable to pay any compensation for damage caused by the ARTEMIS satellite on the surface of the Earth or to aircraft, and for damage due to its faults in space. This will also cover the payment of any damages and involvement of ESA in any proceedings in the latter’s capacity of a launching state according to the UN Outer Space Treaty and the Liability Convention.

• The Agency does not intend to transfer the property of any equipment of the

ARTEMIS ground segment as described in Appendix C or to put such equipment at the disposal of the selected operator in any other way. It is the selected operator’s responsibility to carry out on his own or to procure the satellite operation services currently provided through the ARTEMIS ground segment (see also section 6.3 of the present document).

• The selected Operator shall be responsible for the safe de-orbiting of the ARTEMIS

satellite and bear all costs related to the de-orbiting.

• The specific undertakings of the selected Operator (see 6.5) shall also be laid down in this contract.

• The selected Operator may make a proposal for the provisions of data relay services

for ATV 4 and 5 and EGNOS. In this case, the commercial, financial and legal conditions under which such services would be provided shall be defined.

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• The orbital slot associated to the ARTEMIS satellite, which is currently registered as "F/ESA” and administered by France, will have to be re-registered with the national administration chosen by the selected operator. The selected Operator is responsible for undertaking all the necessary steps with the national administration of his choice in order to register the filing in ITU. The Agency shall not be responsible for obtaining the support of any national frequency administration and shall not be obliged to support the selected operator in its negotiations or proceedings with national frequency administration(s). This is the exclusive responsibility of the selected Operator.

• The selected Operator will also be responsible for taking all necessary steps required by the applicable national administrations of those jurisdictions to which the ARTEMIS satellite may provide coverage, as may be necessary or appropriate to secure and maintain its rights to utilize the orbital slot. In this respect all required activities related to frequency licensing and coordination with other national administrations and satellite Operators for frequencies shall be performed by the selected operator according to the requirements of the applicable national legislation.

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7 SELECTION PROCEDURE AND EVALUATION CRITERIA

7.1 Selection procedure

The selection procedure will follow the steps further described below. Step 1: Notice of Intent Step 2: Dialogue phase Step 3: Proposal submission Step 4: Final selection Step 5: Contract signature

7.1.1 Step 1: Notice of Intent

Following the issuing of this Announcement of Opportunity, interested parties are requested to submit a Notice of Intent indicating their firm intention to submit a proposal and providing a first set of information as defined in the template provided in Appendix A. There will be no pre-selection done among the Bidders on the basis of content of the Notice of Intent. The completed Notice of Intent shall be submitted by e-mail to the address indicated in the cover letter. Please note that further communications (provision of more detailed data, further questions, broadcast of general-interest Q&A and dedicated dialogue sessions) will only be done with Bidders having submitted a Notice of Intent duly signed by the deadline defined in section 7.2.

7.1.2 Step 2: Dialogue phase

Additional information regarding the services currently provided by ARTEMIS, the satellite operational status and the frequency filing coordination status will be provided to the Bidders with confirmed interest (by means of the Notice of Intent defined in Step 1) subject to the signature of a mutually agreed NDA. It is recognised that some interactions with the Bidders may be required during the Bidding phase. ESA therefore offers support to Bidders in providing further clarifications (including needed information from TAS-I/Telespazio and RSS aimed at better shaping the Bidder’s offer). Questions shall be addressed via e-mail to the address stated in the cover letter. Questions will be collected during this period and will be answered on an individual basis as soon as possible. Dialogue sessions may be organised individually with each Bidder during this phase on the Bidder’s request. However, the results of such dialogue sessions shall never be interpreted as changing the terms and conditions of the present Announcement of Opportunity. Bidders may also contact TAS-I/Telespazio, currently in charge of the ARTEMIS SCC function, and perform the related due diligence. In that case, the outcome of this due

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diligence shall be presented as part of the proposal. ESA shall be informed of any discussion/meeting organised between the Bidder and TAS-I/Telespazio and shall be granted the right to attend. The same approach applies with Redu Space Services RSS currently providing the ARTEMIS Mission Control Facility function.

7.1.3 Step 3: Proposal submission

By the defined deadline (see calendar in section 7.2) a full proposal will need to be submitted, with the content defined in section 8).

7.1.4 Step 4: Final selection

An evaluation of the submitted proposal will be done that may result in a down selection. Initial negotiations may be undertaken with one or several Bidders to allow them to propose a best and final offer at the end of this process. The criteria as defined in section 7.3 will be used to rank the proposals.

7.2 AO process schedule

The schedule associated to the AO is defined in the following table: Step Event Date/duration 1 Notice of Intent 31 st January 12h00 (CET ) 2 Technical + Contractual dialogue 1 st February to 14th March 3 Proposal submission 1st April 4 Final selection 30th May

Table 1: AO process schedule

7.3 Evaluation criteria

Through this Announcement of opportunity the Agency is looking to obtaining maximum benefits for the Agency and the European space telecom industry. For the final selection, the following evaluation criteria will be used:

1. Consortium experience in Satellite Operation and Service provision; 2. Credibility of the operation and deorbiting plans of the ARTEMIS satellite proposed

to be executed by the Bidder after taking ownership of ARTEMIS; 3. Credibility and Benefits for ESA and European Space Telecom Industry of the

Bidder plan of activities. 4. Compliance with contractual and legal conditions.

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8 PROPOSAL GUIDELINES

8.1 General tender conditions

The proposal and all correspondence relating to it shall be in English. The proposal shall specifically state a period of validity of 4 months from the closing date for the receipt of tenders. Any document submitted in reply to the AO shall become the property of the Agency. The Agency will use commercially sensitive or proprietary information solely for the purpose of the evaluation of the proposal and the selection. Expenses incurred in the preparation and dispatch of the proposal will not be reimbursed. This includes any expenses connected with the dialogue with TAS-I/Telespazio and/or RSS and to the visits organised by ESA to the SCC and MCC facilities. The AO does not bind the Agency in any way to place a contract. The Agency reserves the right to issue amendments to the AO. Prior to submitting the proposal, the Bidder is requested to complete and send a Notice of Intent form no later than the date indicated in section 7.2. The template for this document is provided in Appendix A.

8.2 Proposal content

The Bidder shall include at least the following content (any additional relevant information deemed necessary by the Bidder may be included in its proposal). Some of those sections may not be relevant depending on the intended re-use of ARTEMIS proposed by the Bidder. In case a section is not considered to be relevant, the Bidder is invited to indicate so.

1. Signed Cover Letter including:

§ A summary of the intended use of the ARTEMIS satellite and frequency filing(s) and of the proposed activity plan benefiting the European Satellite Telecom Industry;

§ The name, telephone / fax number and e-mail address of the bidder's contact person to whom all communications relating to its proposal should be addressed;

§ The contact details of the persons responsible for technical and contractual matters;

§ The name and function of the legal representative that would sign the contract on behalf of the bidder;

§ The name of the author(s) of the proposal.

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2. Detailed description of the intended operations of the ARTEMIS satellite including: § Operational concept; § Identification and description of the ground entities (companies and physical

premises) involved and their respective functions; NB: the Bidder is invited to report the results of the due diligence with TAS-I and RSS and indicate if the operations of the ARTEMIS satellite will be continued with those entities or if the Bidder will take over this role by other means;

§ Intended orbital relocation; § Service(s) to be provided through the use of ARTEMIS satellite including types of

services, frequency band used, coverage, etc.; § Intended service duration; § Satellite replacement strategy; § De-orbiting plan.

3. Intended use of the ARTEMIS filings including:

§ Identification of the Filing(s) to be re-used; § Evidence from a selected National Frequency Administration agreeing to become

the administrator of the relevant ARTEMIS filing.

4. Provision of ATV and EGNOS services proposal including (at Bidder’s discretion): § Operational concept; § Service fees; § ATV and EGNOS Service Level Agreement status of compliance.

5. Proposal for activities benefiting European Satellite Telecom Industry:

§ The proposal should include concrete evidence of the execution of this plan.

6. Management and contractual proposal including: § Industrial organisation (entities and their role); § Relevant Background information on the entities involved (in particular for

satellite operation and service provision).

7. Statement of compliance with the contractual conditions set forth in chapter 6.6 of the present AO.

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APPENDIX A NOTICE OF INTENT FORM

SUMMARY PAGE

Name of the Bidder company: Contract manager name: Technical manager name: Mailing address: Mailing address: Tel.: Tel.: Fax: Fax: E-mail: E-mail: Statement of firm intention to submit a proposal signed by an authorised representative of the bidder. Description of the intended use of the ARTEMIS satellite: If this section is relevant, please include at least:

- a description of the service/utilisation of the ARTEMIS satellite; - the expected duration of the use of ARTEMIS satellite; - if orbital re-location is required, state to which location;

Description of the intended used of the ARTEMIS filings: If this section is relevant please include at least:

- Which bands in the three filings are intended to be exploited; - Whether a replacement satellite is planned; - Which National Frequency Administration would be selected to become the

administrator of the ARTEMIS filing(s); Description of the planned activities benefiting European Space Telecom Industry: Provide as much details as possible on the planned activities. ATV/EGNOS services: Indicate if the Bidder is considering providing ATV/EGNOS services. Note: this document should be approximately 10 pages long.

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APPENDIX B ARTEMIS TECHNICAL DESCRIPTION

At this stage of the AO, the information provided here below is also available in the public domain. More detailed technical information will be provided to the Bidders who have returned a completed and duly signed Notice of Intent (Appendix A).

Satellite

Figure 1: ARTEMIS satellite

The S/C structure consists of a box-shaped three-axis bus of Italsat heritage (Alenia Spazio bus family). The primary structure consists of the central cylinder (aluminum honeycomb skinned with carbon fiber), the main platform, the propulsion platform, and four shear panels. The secondary structure is made up of the N/S radiators, the E/W panels, and the Earth-facing panel. The central propulsion module houses the propellant tanks, LAE (Liquid Apogee Engine), the East panel with the L-band antenna feed, the West panel with the IOL (Inter Orbit Link) antenna. The two antenna reflectors (2.85 m diameter) for IOL support are dominant features of the S/C structure. S/C attitude is measured by Earth/sun sensors and gyros. Reaction wheels serve as actuators. Thrusters of an RCS (Reaction Control System) are used for wheel off-loading. The UPS (Unified Propulsion System) employs a bi-propellant system of a single 400 N LAE for insertion into GEO. The propellants are stored in two Cassini-type 700 liter tanks. E/W positioning is maintained by a 10 N RCS (Reaction Control System) engine. N/S positioning is maintained by electric ion thrusters. The IPS (Ion Propulsion System) comprises two thruster assemblies, RIT (RF Ion Thruster) and EIT (Electro-bombardment

- 24 -


Ion Thruster). Each is powered and monitored separately, but a common propellant supply is used (40 kg of xenon), 600 W of input power is needed for operation.. S/C electric power of 2.8 kW (at equinox after ten years to a 42.5 VDC bus) is provided by two solar wings (span of 25 m). BSR (Back Surface Reflecting) solar cells are mounted on each of the two solar wings. Two NiH2 batteries provide energy of 60 Ah for eclipse protection. A S/C design life of 10 years is provided. The S/C launch mass is 3100 kg (550 kg payload, 1538 kg propellant). At the platform level, ARTEMIS combines all the tasks classically associated with the data handling and attitude and orbit control subsystems into one subsystem, the ICDS (Integrated Control and Data System). The ICDS in turn is comprised of the following elements (all units have a redundancy):

• OBCU (On Board Computer Unit) • IRES (InfraRed Earth Sensor) • RIGA (Rate Integrating Gyro Assembly) • PSSA (Precision Sun Sensor Assembly) • MWA (Momentum Wheel Assembly) • RU-A (Remote Unit A), RU-B (Remote Unit B) • OBDH (On Board Data Handling) bus (ESA standard). The OBDH bus provides the

communications media between the OBCU, and all platform and payload units. The attitude and orbit control functions within ICDS make use of additional actuators which are not part of the ICDS, namely the RCS, the LAE, and the ion thrusters plus their alignment platform (ITAM).

- 25 -


Spacecraft Characteristics

Mass at launch, power 3100 kg, 2.5 kW

S/C size: height, length, width

4.8 m, 25 m (solar array tip-to-tip), 8 m (antennas deployed)

Design life 10 years

Orbital position 21.5º E (GEO)

Communications: Data Relay Payload

Coverage Approximately 65% of orbits up to 1000 km altitude

Feeder/downlink coverage Western Europe

Inter-orbit link (S-band 2 GHz)

Up to 1 Mbit/s in the forward direction (i.e. ARTEMIS to low altitude spacecraft). Up to 3 Mbit/s in the return direction (i.e. low altitude spacecraft to ARTEMIS)

Ka-band (23/26 GHz) 10 Mbit/s in the forward direction 3 x 150 Mbit/s in the return direction

Optical link (800 nm) 2 Mbit/s in the forward direction 50 Mbit/s in the return direction

LLM (L-band Land Mobile) Payload

Coverage Europe, North Africa & Middle East (one European beam and three spot beams)

Frequency bands 1.5 GHz (L-band) to/from mobiles 12/14 GHz (Ku-band) to/from fixed earth stations

Voice channels Up to 662 bi-directional

Mobile terminal antenna 20 cm x 40 cm

Navigation Payload EGNOS

Coverage Global (specifically Europe)

Mass, power 25 kg, 110 W

Antenna L-band to user: 45 cm diameter horn antenna

Frequency bands Downlink: 1.575 GHz (L-band, L1 GPS) & 12.748 GHz (Ku-band) Uplink: 13.875 GHz (Ku-band)

Table 2: ARTEMIS satellite main characteristics

- 26 -


SILEX (Semiconductor Intersatellite Link Experiment) payload

SILEX is an ESA laser experiment built by MMS, France (now Astrium Satellites SAS). SILEX consists of two optical terminals, namely OPALE (Optical Payload for Intersatellite Link Experiment) located on ARTEMIS, and PASTEL (PAssager SPOT de Técommunication Laser) on-board SPOT-4. The objective is to beam data at rates of 50 Mbit/s (bit error rate of <10-6) from the transmitter terminal on SPOT-4 in LEO - to the receiver (OPALE) on ARTEMIS for subsequent relay via feeder link to the SPOT ground segment in Toulouse. The SILEX terminal on-board ARTEMIS is also being used to support a second LEO experiment, namely an IOL between ARTEMIS and OICETS (Optical Inter-orbit Communications Engineering Test Satellite) of NASDA. PASTEL (Passager SPOT de Técommunication Laser). A joint ESA/CNES passenger demonstration experiment. PASTEL is a prototype high data-rate intersatellite transmission system based on laser technology. The objective is to transmit imaging data from SPOT-4 to ARTEMIS. The aim of the experiment is to validate the PASTEL concept design in an operational environment. PASTEL is a gimbal-mounted assembly consisting of a telescope, an optical bench with a fine pointing system, communication detectors with avalanche photodiodes, a thermal control system for precision temperature control, a two-axis gimbal mechanism, and the launch locking mechanisms needed during the launch phase. The telescope mirrors and main structural elements are made of Zerodur. The acquisition and tracking sensors use CCD detectors. The laser diodes are of the GaAlAs type. The SPOT-4 - ARTEMIS optical links operate at wavelengths of 830 nm. The peak output power is 160 mW (60 mW continuous operation), the beamwidth is 0.0004º. Data to be transmitted include: HRVIR image data, pseudo-noise (PN) code, PASTEL telemetry. OPALE (Optical Payload for Intersatellite Link Experiment) terminal, mounted on the geostationary satellite ARTEMIS (a GEO terminal). The receiver employs Si-APD (Silicon Avalanche Photodiode) detectors and a low-noise trans-impedance amplifier of 1.5 nW useful receiver power.

SKDR Payload (S/Ka-band Data Relay)

The objective of the IOL antennas (2.85 m diameter) is to track a LEO user satellite via either loaded table values and/or error signals - and to receive up to 450 Mbit/s of data in the Ka-band, or up to 3 Mbit/s in S-band for relay via the feeder link to Earth (return link operation). Up to 10 Mbit/s in Ka-band and 300 kbit/s in S-band may be transmitted by ARTEMIS to the LEO satellite (forward link operation). In addition, ARTEMIS broadcasts a 23.540 GHz beacon to help the LEO satellite to track it. A single Ka-band transponder (plus one backup) provides return/forward frequencies of 25.25 - 27.5/23.2 - 23.5 GHz links in Rx/Tx, adjustable EIRP (Effective Isotropic Radiated Power) of 45-61 dBW, G/T of 22.3 dB/K, up to 150 Mbit/s each of the three channels LEO to ARTEMIS (return link), and up to 10 Mbit/s from ARTEMIS to LEO (forward link). RH/LHCP on command.

- 27 -


One S-band transponder (plus one backup) provides return/forward frequencies of 2.200-2.290/2.025-2.110 GHz links in Rx/Tx, adjustable EIRP 25-45 dBW, G/T of 6.8 dB/K. The bandwidth is 15 MHz. Up to 3 Mbit/s of data can be transmitted in a single channel from LEO to ARTEMIS (return link), and up to 300 kbit/s can be transmitted from ARTEMIS to LEO (forward link). RH/LHCP on command. Feeder link of SILEX and SKDR: Three transponders (plus one backup) act as ground-ARTEMIS links for SILEX and SKDR. The feeder Ka-band frequencies are: 27.5-30/18.1-20.2 GHz for Rx/Tx. The EIRP is 43 dBW, G/T of 0 dB/K, use of 234 MHz bandwidth, linear vertical polarization.

NAV Payload

The objective is to provide enhanced navigation performance in terms of accuracy and integrity (with the required levels of availability and continuity) over the ECAC (European Civil Aviation Conference) region. The ECAC coverage area is from 30º W to 45º E and from 25º N to 75º N. The EGNOS payload on ARTEMIS uses the Ku-band in the uplink and downlink (for S/C - fixed user communication in the ground segment). The uplink frequency is allocated at 13.875 GHz, and separate from the LLM feeder link frequency, while the downlink of the navigation payload is shared with the LLM channels (12.748 GHz). The transmitted EGNOS wide-area service signal is the GPS L1 frequency at 1575.42 MHz (L-band). The total mass of the navigation payload, including structure, thermal control hardware and the DC harness, is 25 kg. Its total power consumption is about 110 W. Receive frequency 13.875 GHz (Ku-band)

Transmit frequencies 12.748 GHz (Ku-band), 1575.42 MHz (L-band)

Useful bandwidth 4 MHz

G/T [(receiver) Gain / (noise) Temperature] >-2.3 dB/K

EIRP (Effective Isotropic Radiated Power) >17 dBW for Ku-band; >27 dBW for L-band

Polarization LP for Ku-band, RHCP for L-band

Frequency stability 2x 10-12 (10s); 10-9 (24 h); 2 x 10-7 (life)

Table 3: ARTEMIS NAV payload sCharacteristics

- 28 -


LLM Payload

The objective of the communications payload is to permit two-way communications, via satellite, between fixed Earth stations and land mobiles, such as trucks, trains or cars, anywhere in Europe and North Africa. The LLM receives the signals transmitted by the fixed users in Ku-band (14.2 GHz) and transmits them at L-band (1550 MHz) to the mobile users (forward link). The return link establishes the connection from the mobile user at L-band (1650 MHz) to the S/C, and at Ku-band (12.75 GHz) from the S/C to the fixed user in the ground segment. About 400 bi-directional user links can be established simultaneously. ARTEMIS carries two antennas of 2.85 m diameter and a multiple element feed for pan-European coverage and three European spot beams. Three 1 MHz plus three 4 MHz SSPA (Solid-State Power Amplifier) channels, provide 400 2-way circuits with an EIRP>19 dBW. The on-board L-band transmits to terminals (users) in the ground segment at 1550 MHz and receives data at 1650 MHz. A Ku-band feeder link at 14.2/12.75 GHz Rx/Tx transmits the data to the home stations. All channels are fully tunable and most commandable for LH/RHCP support.

Ground Segment

The ARTEMIS Programme element also included the development of the Ground Segment Infrastructure including both the Mission Control Centre (AMCF: ARTEMIS Mission Control Facility, in Redu) and the Satellite Control Centre in Fucino. More details is provided in the Appendix C

- 29 -


APPENDIX C ARTEMIS OPERATIONS DESCRIPTION

ARTEMIS operations in geostationary orbit are unconventional due to the need of preserving the feeder link coverage in the lack of North South station keeping. The harmonic bias compensation is therefore active for the vast majority (exceptionally disabled by spurious events) of the time and the satellite inclination has been growing steadily. An overview, including all Users’ interfaces for current and past missions, is provided in the following scheme.

Figure 2: ARTEMIS user interface scheme

Hereafter the main capabilities of the Satellite Control Centre and of the Mission Control centre are listed.

ARTEMIS Satellite Control Centre (Fucino)

• Controls and monitors the ARTEMIS satellite operating through the Ka-band TTC

station or the S-band back-up TTC station in Fucino. • Responsible for the execution of all satellite operations. • Responsible for all satellite operations needed to configure the payload according to

the payload operation schedule received from the AMCF. • AOCC is manned 24 hours per day continuously. • No operational contact between the Users and the AOCC.

- 30 -


ARTEMIS mission control centre (Redu)

• Responsible for the detailed scheduling of ARTEMIS payload utilisation • Interfacing with the ARTEMIS Control center in Fucino for payload configuration

request. • Receiving the service requests from the Users. • Managing the conflicts between Users for service attribution. • Interfacing with the Users for the day to day operations. • Producing the planning products for the users as the Detailed Assignment Plan. • Exchanging ancillary data such as orbit predictions with users. • Managing emergency service requests • Coordinating with users anomaly investigations and fault isolation. • Manned 8 hours per day, 5 days per week during normal working periods, can be

extended to meet the requirements of the users for critical operations.

Figure 3: ARTEMIS MCC at Redu

- 31 -


Users interfaces

In case of anomaly, AMCF issues an Operations Status Message (OSM) and unavailability reports and provides statistics on the utilization of the payload. AMCF manages also the database with the Users characteristics and the ARTEMIS payload configuration details for each user. The TC for payload configurations are generated automatically at the AOCC based on the payload schedule received from AMCF generated once per week and divided by the AOCC in slice of 8 hours of on-board schedule. ICD documents are produced for each User which includes the requirements for the mission management and operations of the ARTEMIS services.

ESA Earth Terminal and IOT facilities (Redu)

• Real time monitoring of the payload operations. • Forward and return link data transmission and acquisition via a feeder station • Satellite in orbit payload testing. • Monitor in real time correct data transmission and receiving the ARTEMIS

telemetry. • Acting as a feeder link station with up to two forward channels and up to 4

simultaneous return channels. • The In Orbit Tests facilities include several antennae operating in all data relay

frequency bands simulating LEO satellite.

- 32 -


TMS1-M (RED-2)

Antenna

Figure 4:Redu 2 13.5m antenna (TMS-1M)

The Redu 2 (TMS-1M) is a 13.5m Ka-band full monition antenna and is part of the EET facility, which simultaneously supports Data relay and Ranging functions. The antenna system has the following capabilities: -

• Provides two simultaneous channels data relay forward feeder link at 30 GHz converted from 750 or 70 MHz.

• Provides four simultaneous channels data relay return feeder link at 20 GHz converted to 750 or 70 MHz.

• Provide data relay test loop by means of a synthesised TLT in order to verify transmit and receive function of any single transmit and receive channel.

• Provide a receive and a transmit port (20 and 30 GHZ) respectively) interfacing to the RRT.

• Receive the satellite pilot and provide it to the EET. The EET comprises the TMS-1M antenna system, the modems, fiber optic switch, the test equipment’s (BER, Spectrum Analyser, Pilot Frequency Counter) EET Data Patch and the M&C computer.

- 33 -


Description

Tracking The tracking subsystem is a monopulse type. The tracking chain is part of TMS-1M antenna system and is composed of the following items:

• A mode generator and combining network • A low noise amplifier for the error signal • Two dual channel tracking down converters • A dual channel tracking receiver • The antenna control unit • The Az and El antenna servos

Transmit Chains The TMS-1M transmit s/s has two complete chains (HPA+U/C) that can feed the antenna TX port simultaneously (frequency combined) or can be operated transmitting only one of them (with a EIRP 3.5dB higher than when combined). Each HPA is a 100W TWTA with an internal SSPA. The associated U/C has incorporated a PIN attenuator to provide EIRP adjustment of at least 20dB from maximum and in steps lower than 1 dB.

Receive Chains The TMS-1M and RRT have receiver chains with a common part (from the feed RX port up to the divider after the LNA) and an individual part (from the Ka band down converter input up to the IF port). These common elements are included in the TMS-1M The 20GHz section comprises of the following elements (starting from the feed port): -

• A waveguide coupler to inject the receive chain the TLT output (either from TMS-1M or RRT).

• Two WG switches to select LNA1 or LNA2. • Two LNA’s with 1.5dB noise figure. • A wave guide coupler to pick-up a sample of the received pilot signal in order to

provide the sum signal to the auto-track s/s. • Three rotary joints that allow the azimuth, elevation and polarisation movements of

the rigid waveguide path to connect with the 2-way divider located in the first floor. After that one 4-way divider provides two outputs for the RRT Down Converter as well as one SHF test output; the other 4-way divider drive the four Ka-band Down Converters of the TMS-1M.

Calibration This subsystem contains two different parts: the TX power measurement arrangement and a test loop translator. The first is devoted to measure the EIRP of the transmitted carried and the second one to operate the station in a closed loop via the TLT (to verify any transmit/receive channel function of TMS-1M).

- 34 -


Figure 5 : Redu-2 Block Diagram (TMS-1M)

- 35 -


TMS-4

TMS-4 measures the performance of geostationary satellites in the 12 to 14 GHz band (Ku-Band), with the support of the 9.3 m antenna, which can transmit in dual linear polarisation and in two frequency bands (12.96 to 13.29 GHz and 13.96 to 14.30 GHz); in addition, it is able to receive the 12.46 to 12.79 GHz range, also in dual linear polarisation (X and Y). TMS-4 is remotely controlled from the Test Monitoring Room (TMR).

Antenna

Figure 6: TMS4 Antenna

TMS-4 has a Cassegrain 9.3m antenna with a 92cm sub-reflector. It has a gain at interface RX IOT point of 59.6 dBi at 12.75 GHz and of 61.7 dBi at interface TX IOT point at 14.5 GHz. The pointing range is 90°-270° in azimuth, 0°-90° in elevation and 360° in polarisation. It has three pointing modes: Program track, slaved to TMS5 and slaved to TMS6.

Description Each HPA can work in fixed gain mode (FGM) or in automatic level control mode (ALC). Some switches act as attenuators at the HPA’s output to output a fairly high power from the HPA’s in order to minimise their noise contribution when low EIRP is required for up-link to the satellite.

- 36 -


An HP-UX workstation is located in the antenna shelter. This computer controls and monitors all the station equipment via HP-IB buses or LAN.

Characteristics Transmit:

• Transmit frequency bands: 12.96-13.29 GHz and 13.96-14.3 in TX/RX mode, using up-converters. 12.75-14.5 GHz in TX only mode, using SHF synthesisers.

• Number of simultaneous carriers: two, one on each polarisation or both on one polarisation after high power combining.

• Maximum EIRP: > 84 dBW each carrier > 81 dBW when combined • EIRP range: maximum to 80 dB down spread over 4 ranges involving two high

power attenuators • EIRP control: fast ALC loop or gain control • EIRP accuracy: ± 0.5 dB • TWTA output power: 500 W • HPA intermodulation: 27 dBc at 10 dB output backoff • HPA AM/PM conversion: 4°/dB at 500 Watts • HPA noise density: -75dBW/4kHz • Power measurement accuracy: ± 0.2 dB • Power versus frequency:

± 0.2 dB/80 MHz in ALC mode ±1.25 dB/full band in gain mode

• IF frequency and bandwidth: 750 MHz ± 80 MHz when using up-converters • Frequency stability: derived from HP8662 or R/S SMP SHF synthesiser (5.10-

10/day) Receive:

• Receive frequency band: 12.46-12.79 GHz in TX/RX mode only • G/T (clear sky, 30° elevation): > 31.0 dB/K • Flux measurement range: -115 dBW/m2 to –165 dBW/m2 • Flux measurement accuracy: ± 0.4 dB • Pilot power accuracy: ± 0.3 dB • Band flatness: ± 0.5 dB over 80 MHz • Group delay overall: ± 3 nS over 80 MHz • IF frequency and bandwidth: 750 MHz ± 80 MHz • Frequency stability: derived from HP8662 synthesiser (5.10-10/day)

- 37 -


DiplexerX

X

X

Y

YY

HPA1

HPA2

+

20 dB

40 dB

20 dB

40 dB

SW19

SW20

SW16

SW17

SW22

SW21H

P848

4A

HP8

484A

30 d

B at

t.

HP438A

SW5

SW4 SW6

HP8

481A

HP8

484A

HP438A

30 dB

Pin att

Pin att

ALC unit

ALC unit

SHF synt 1SMP-02

SHF synth 2SMP-02

Up-conv. 1

Up-conv. 2

40 dB

40 dB

35 dB

35 dB

Auxilliarydown-conv.

HP8662synthesiser X 14

Testtranslator

x 10

HP8662synthesiser

Down-conv. 1

Down-conv. 2

X 10HP8662synthesiser

HP8

481A

HP8

484A

HP438A

30 dB

C3C4

10 dB

10 dB

10 dB

10 dB

20 dB

C9

C1

C2C6C5

70 dB

70 dB

HP8

481

HP436

HP8

481

HP436

C23

C22 65 dB

65 dB

C21

C20

C19

C18

35 dB

35 dB

10 dB

10 dB

SW13

SW12

SW11

SW10SW9

SW8

SW18

SW3

SW7

SW23

SW28

SW29

3 dB

HP8566BSpectrumAnalyser

TMR interface

21.4 MHz

750 MHz

750 MHz

Splitter

Splitter

AM

PM

PM

AM

AM demodulated tone

Prime and backup MAM power meters


Gain = 50 dBT = 70 K

O/P IP = 20 dBm

LNA1

LNA2

750 MHz

750 MHz

Modulation tone

750 MHz

TMS4 block diagramFile name: TMS4.vsd Updated: GKrev. 29/08/2002

AB

B A

BA

Diameter: 9.3 mAssumed antenna gain (at TX/RX interfaces): - TX: 61.7 dBi @ 14.500 GHz - RX: 59.6 dBi @ 12.750 GHzMaximum EIRP: 84 dBWG/T: 31.0 dB/K

SW33

SW31

SW32

SW30

SW1 SW2

OMTPolariser

X

Y84 dBW

-113 dBW/m2

SGH

30 dB6

dB

3 dBm

3 dBm

30 dB

20 dB

20 dB

3 dB

6 dB

HP8

481

HP436

HP8

481

HP436

3 dB 3 dBm

DL1

DL2

500W TWTA

500W TWTA

SW35

SW34

3 dB

A702

A701

A703

A705

A707

B718

B719

14 dBm

14 dBm

-23 dBm

-24 dBm

HP8592ASpectrumAnalyser

T6 dB

SW3b

SW25

SW54

SP4

a b

a b

SP2

C10

C11

C13

C12

SP3

SP5

SP1

SW36SW37

SW39SW38

SW40

SW42

SW41

SW43

C15

C14

C17

C16

C24

C26

C27

C25

SP6

SP7

a

b

a

b

A706

B715 B715

B714 B714

TBD dBmTBD dBm

TBD dBmTBD dBm

TBD dBm

TBD dBm

TBD dBm

TBD dBm

Hpib bus

A : t4hpibaB : t4hpibb

Frequency plan

Tx : Tx only mode : 12.75 -> 14.50 GHzTx / Rx mode : 12.96 -> 13.29 GHz 13.96 -> 14.30 GHz

Rx : 12.46 -> 12.79 GHz

3 dB

SW53

PINatt/mod

SW55

Historyrev GK: 29-Aug-2002 : Pin mod config + switch 55

Figure 7 : TMS4 schema

- 38 -


TMS-5

The 9.3 m antenna can transmit in dual circular polarisation on six selectable channels with 80 MHz bandwidth, spread over the 17.3 to 18.1 GHz band; in addition it can receive in dual circular polarisation in the 11.7 to 12.5 GHz band.

Antenna

Figure 8 : TMS-5 antenna

TMS-5 has a Cassegrain 9.3m antenna with a 92cm sub-reflector. It has a gain at interface RX IOT point of 58.8 dBi at 12.75 GHz and of 61.3 dBi at interface TX IOT point at 17.5 GHz. The pointing range is 90°-270° in azimuth, 0°-88° in elevation and ±50° in polarisation.

Description Each HPA can work in fixed gain mode (FGM) or in automatic level control mode (ALC). Some switches act as attenuators at the HPA’s output to output a fairly high power from the HPA’s in order to minimise their noise contribution when low EIRP is required for up-link to the satellite. An HP-UX workstation is located in the antenna shelter. This computer controls and monitors all the station equipment via HP-IB buses or LAN.

- 39 -



• Transmit frequency bands: 17.3-18.4 GHz (Linear Pol.) 17.3-18.1 GHz (Circular Pol.)

• Number of simultaneous carriers: two, one on each polarisation or both on one polarisation after high power combining

• Maximum EIRP: > 82 dBW each carrier > 79 dBW when combined

• EIRP range: maximum to 80 dB down spread over 4 ranges involving two high power attenuators

• EIRP control: fast ALC loop or gain modes • EIRP accuracy: ± 0.5 dB • TWTA output power: 300 W • HPA intermodulation: > 27 dBc at 30 Watts output • Power measurement accuracy: ± 0.2 dB • Power versus frequency:

± 0.2 dB/80 MHz in ALC mode ± 1.25 dB/full band in gain mode

• IF frequency and bandwidth: 750 MHz ± 80 MHz Receive:

• Receive frequency band: 10.70-12.75 GHz • G/T (clear sky, 30° elevation): > 34 dB/K • Flux measurement range: -115 dBW/m2 to –165 dBW/m2 • Flux measurement accuracy: ± 0.4 dB • Pilot power accuracy: ± 0.3 dB • Band flatness: ± 0.5 dB over 80 MHz • Group delay overall: ± 0.5 nS over 100 MHz • IF frequency and bandwidth: 750 MHz ± 80 MHz

- 40 -


HPA1

HPA2

R&S NRVD

Pin att

Pin att

ALC unit

ALC unit

SHF synt 1SMP-02

SHF synth 2SMP-02

Up-conv. 1

Up-conv. 2

C1040 dB

C1240 dB

35 dB

35 dB

Auxilliarydown-conv.

HP8662synthesiser

X 14

R&S SMGsynthesiser

R&SNRV-Z52

-30/+20dBm

R&S NRVD

HP8

481

HP436

HP8

481

HP436C19

C18

10 dB

10 dB

SW13SW12

SW11

SW10 SW9 SW8

SW3

SW23

SW36

SW37

HP8566BSpectrumAnalyser

TMR interface

21.4 MHz

Splitter

Splitter

PM

PM

AM

AM demodulated tone



Diameter: 9.3 mAssumed antenna gain (at TX/RX interfaces): - GTx:62.2 dBi @ 17.3 GHz - GRx:58.1 dBi @ 10.7 GHzMaximum EIRP: 84 dBWG/T: 34 dB/K

750 MHz

750 MHz

Modulation tone

SHF synthSMP-02

20 dB

Gain = 50 dBT = 70 K

O/P IP = 20 dBm

- 18 dBm

LNA1

LNA2

HP8

484A

HP8

484A

30 d

B at

t.

HP438A

SW5

SW4 SW6

C9

SW1 SW2

C23

C22 60 dB

60 dB

C21

C20

40 dB

40 dB

SW18

SW7

TLTmodule

0-60 dBTLT

C3

10 dB

10 dB

C5

R&S FSPspectrum analyser

R&S FSPspectrum analyser

Monitoring LAN

Monitoring LAN

C1

C2

53 dB

53 dB

- 68 dBm

LNA3

Trackingdown-converter

Trackingreceiver ACU

X-L Y-R

OMTTrk couplerPolariserDiplexer

84 dBW

-113 dBW/m2

Trk

20 dB40 dB

20 dB

40 dB

SW19

SW20SW16

SW22

SW21

+

SW17

Down-conv. 1IF: 140 MHz

Down-conv. 2IF: 140 MHz

3 dBsplitter

Frequencyconverter 2

Frequency converter 1

3 dBsplitter

TMS5 block diagramFile name : TMS5.vsdRev. date : 27/Sep/2005

Pin AMmodulator

750 MHz

750 MHz

Low IF

3 dB

3 dB6

dB

15 dBm

20 dB

3 dB

6 dB

3 dB 14 dBm

20 dB

30 dB

30 dB

HP8

481

HP436

HP8

481

HP436

ps5 ps6

ps3ps4

ps2 ps1

SGH

DL1

DL2

300W TWTA

300W TWTA

SW25

SW38

GPTL Aux.DC

GPTL TX2

GPTL RX1

SW28

SW15

SW50

SW51

SW52

SW53

SW54

SW55SP4 SW57

SW58

SW59

SW60

SW61

SW62

R&SNRV-Z6

-60/+13dBm

PM2

50MHz REF.

PM1

R&SNRV-Z52

-30/+20dBm

R&SNRV-Z6

-60/+13dBm

50MHz REF.

GPTL RX2

GPTL TX1

-70/-20 dBm -70/-20

dBm

50MHz REF.

PM3

-67 dBm

20.6dBW

10.7-12.75 GHz0dBm

- 9 dBm

C15

C14

C17

C16

a

C13

24.9dBW

L

R

SW40SW39

SW43

SW42SW41

3 dBhybrid

3 dBhybrid

Y-R X-L

B703

B705

B702

B701

A722

A723

S726/727

S728/729

A707

VXI

Switches driver

????

????

B724

B718

A706

B719

B714 MAM714

B715 MAM715

For G=62dbC/I=55 dB @ 0 dBm O/P

for 2 carriers3rd IP=27.8 dBm

TBC

10 dBm

10 dBm

-37 dBm

-34 dBm

- 38 dBm

- 37 dBm

-13 dBm

- 21 dBm

+ 30 dB SW14

Rx Amp OUT Rx OUT

10 dB

C6

C4

10 dB

Splitter

Splitter

T

SW 3b a

b

C11

SP2

SP3

a b

SP1

SP5

SW56

b

a

b

Hpib bus

A : t5hpibaB : t5hpibb

610 MHz

140 MHz

SP 6

SP 7C14

C16

SP8

SP9

SP10 SP11

C25

10 dB

Frequency plan

Tx : 17.30 -> 18.40 GHzRx : 10.70 -> 12.75 GHz

AM9 dBPIN

att/mod SW55

-15 dBm

-15 dBm

-4 dBm

-4 dBm

- 8 dBm

- 8 dBm

10dBm synth nom. level

10dBm synth nom. level

640 MHz

TLO

2dB

LO D/C 1R&S SMP02

LO D/C 2R&S SMP02

140 MHz

A712

A711

Figure 9 : TMS-5 schema

- 41 -


TMS-6

The TMS-6 test and monitoring antenna complements TMS-4 & 5, it has two transmit chains operating in the 27.5 to 30 GHz range, and three reception chains operating in the 18.1 to 20.2 GHz band.

Antenna

Figure 10: TMS-6 Antenna

TMS-6 has a Gregorian 4m antenna with a 1m sub-reflector. It has a gain at interface RX IOT point of 53.2 dBi at 18.1 GHz and of 59.5 dBi at interface TX IOT point at 28.5 GHz. The pointing range is 90°-270° in azimuth, 1°-44° in elevation and ±90° in polarisation. The antenna control system can be set to autotrack mode. In this mode, the antenna is continuously pointed, in azimuth and elevation, to the satellite beacon or signal source.

Description The system is capable of simultaneous RX and TX on dual orthogonal linear polarisation (X and Y) and circular polarisation (LHCP and RHCP). At LNA input, the received level for a nominal –110 dBW/m² flux is –71 dBm. This signal is amplified by the LNA, which has a noise figure of 2.6 dB and a gain of 40 dB, giving an output signal of –31 dBm. The TX subsystem can provide an EIRP of 79 dBW on each carrier. The HPAs can be operated in Automatic Level Control (ALC), Fixed Gain (FG) or ASSC mode. An HP-UX workstation is located in the antenna shelter. This computer controls and monitors all the station equipment via HP-IB buses or LAN.

- 42 -



• Transmit frequency bands: 27.5-30.0 GHz (at antenna interface) 28.5-30.0 GHz (U/C instantaneous BW)

• Number of simultaneous carriers: two, one on each polarisation or both on one polarisation after high power combining

• Maximum EIRP: 79 dBW each carrier in linear or 75.5 dBW when combined

76 dBW each carrier in circular or 72.5 dBW when combined • EIRP range: maximum to 40 dB down spread over 2 ranges involving one high

power attenuator per chain • EIRP control: fast ALC loop or gain control • EIRP stability: ± 0.4 dB • TWTA output power: 250 W • HPA bandwidth: 2500 MHz • HPA C/I3 intermodulation: -15 dBc at 3 dB output backoff

-21 dBc at 6 dB output backoff • HPA AM/PM conversion: 5.5°/dB at 0 dB output backoff

3°/dB at 10 dB output backoff • Power measurement accuracy: ± 0.2 dB • Power versus frequency: ± 0.2 dB/80 MHz in ALC mode up to 29.4 GHz

± 1.25 dB/full band in fixed gain mode up to 29.4 GHz • Group delay response: 2 ns over 80 MHz • Power stability: ± 0.4 dB max. • IF frequency and bandwidth: 750 MHz±80 MHz • Frequency stability: / day (Redu-1 Cesium oscillator) • Phase noise: derived from R&S SME-03E synthesiser

Reference frequency (10MHz)+20*log(N)-4 (N : mult. factor).

- 43 -


Receive:

• Receive frequency band: 18.1-20.2 GHz • G/T (clear sky, 30° elevation): 29.3 dB/K • System noise temperature: 25.8 dBK at LNA input • RX chain overall gain: 60 dB • LNA gain : 40 dB • LNA noise figure: 2.6 dB at 23°C • Flux measurement range: -110 dBW/m2 to –160 dBW/m2 • Flux measurement accuracy: better than 0.6 dB • Pilot power accuracy: better than 0.4 dB • Band flatness: < 1.5 dBp-p over 200 MHz • Group delay overall: < 3 ns over 200 MHz • IF frequency and bandwidth: 750 MHz ± 125 MHz • Frequency stability: 11102 −× / day (Redu-1 Cesium oscillator) • Phase noise: ref. freq(10MHz)+20*log(N)-4 (N: multiplication factor).

Figure 11 : TMS-6 Schema

from M&C(0-5V)

Diameter: 4.0 mAssumed antenna gain (at TX/RX interfaces): - GTx:59.7 dBi @ 29.25 GHz - GRx:55.9 dBi @ 19.15 GHzMaximum EIRP: 81 dBWG/T: 29 dB/K

TMS-6 block diagramFile name : TMS-6.vsdDrawn by : Gerald KUpdated by : Th. DenisRev. date : 09 February 2011

Modulator

3 dB

21 dBW

R&S NRV-Z6

x16

LNA1

LNA2

LNA3

DIV

IDE

R

D/C 1

+3 dBm

D/C 2

D/C 3

SHF TEST4; -??dBm

+3 dBm

Ka BANDtracking D/C

T.L.T.

10.4GHz

S23

-66 dBm

-106/-126 dBm

-71.2 dBm

-3 dBm

R&S NRV-Z55|

R&S NRV-Z55|

30dB

30dB

S33

C9

C8

20dB

+15 dBm

+15 dBm

---- I1xI1y22 dBW

C10 7dB

7dB

AUX D/C

3 dB

3 dB

R&S SME-03E

HP 5087A

R&S SME-03E

R&S SME-03E

U/C 1

U/C 2

IPA

IPA

LO DISTRIBUTION 1

LO DISTRIBUTION 2

LO TEST

S50

S51

S34

+12 dBm

+3 dBm

+3 dBm

R&S NRVDB A

R&S NRVDA

IF DISTRIBUTION IF DISTRIBUTION

Tracking Receiver

C BANDtracking D/C A.C.U.

+3 dBm

+3 dBm

FRONT - END BOX INTERSITE LIINKTMR

COAXIAL 7/8'Rx1 OUT,-10dBm / 750 ±125MHz

Rx1 OUT TEST

Rx2 OUT

Rx3 OUT

Tx1 IN,-15dBm / 750 ±80MHz

Tx2 IN

TEST 1,-15dBm

TEST 2

TEST 3

+10 dBm

+12 dBm

+12 dBm

ANTENNA POSITIONNER

ANTENNA POSITIONNER

R&S SME-03E

R&S SME-03E

Ty Tx

Ry Rx

-66/-86 dBm ANTENNA BUILDING

I2x I2y

S30

S32

S31

S24

-45 / -65 dBm

-25 dBm

-71 / -91 dBm

-51 dBm

0 - 69 dB

-10 dBm-25 dBm

-13 dBm25.4 dBW

S56 S52

S54

S55

S57 S53

HPA 1

ALC 1

HPA 2

ALC 2

MAX

MAX

C1

C2

C3

C4

BUSTMR

TMRBUS

-10 dBm

B

A

AZ

EL

50dB

C14

50dB

C13

S3

|

18.1 - 20.2 GHz-25 dBm

-21.5 dBm

-18 dBm

C16

C15

20dB

20dB

-31.5 dBm

-25 dBm

D

f

S

18.1

- 20

.2 G

Hz

20 -

20.2

GH

z

C12

20dB

+5 dBmPolarizer & Diplexer

D Y-L X-R

X-LY-R

-70.5 dBm

POL

28.5 - 30 GHz

10 MHz

S7

-15 dBm

EIRP 81 dBWFlux -110 dBW/m²(Beac -125 dBW/m²)

350W

350W

AM modulating Input(up to 5.4MHz)

Output

1

2

3

4

2

1

4

3

4

3

2

1

18.1 - 20.2 GHz

0 dB

5 dB

1 dB

HP 105B

10MHz Dist.Amp.

5 MHz

Reference oscillator

# 702

# 705

# 710

# 707

# 701

70 210 00

50 600 00

74 100 00

PILOT

IFIF2

LO2LO

IFIF1

LO1

LO

RF OUT

RF OUT

2

3

4

1

40dB HPL3

C7TEST 5

MPL1HPL1

C5S120dB

MPL2HPL2

C6

S2 20dB

S19

S21

S18

S16

S17

24.7

dB

W

4

3

2

1

2

3

4

1

2

3

4

1

2

1

4

3

4

1

2

3

4

3

2

1

2

3

4

1

1

4

3

2

ref.

ref.

ref.

ref.

ref.

ref.

ref.

ref.

5 MHz

All connections names - tbi

# 704

# 703

+10 dBm

C11

20dB

Frequency plan

TX : 28.5 -> 30.0 GHz

RX : 18.1 -> 20.2 GHz

Revision history :

TD: 21/01/2003: added frequency plan and MAM power meter.TD: 09/02/2011: added circular/linear switches.

MAM POM 1HP 436AMAM BUS 714

MAM POM 2HP 436A

MAM BUS 715

HP 8486A

HP 8486A

C mam

C mam

3 dBhybrid

3 dBhybrid

S39 S40

S42 S41

- 44 -


TMS-L

Three transportable stations TMS-L2 and TMS-L3 allow to carry out spot beam measurements. They can be sited at different locations. The station includes a set of instrumentation located in the shelter close to the antenna, but is also connected to the L-band payload test laboratory where a complete set of instruments is available. The main purpose of this L-band station is to measure in-orbit satellite payload performances.

Figure 12 : TMS-L antenna

Antenna

TMS-L2 as well as L3 is a parabolic 2.4-metre antenna that can be oriented from 88-272 degrees in Azimuth, 1-66 degrees in elevation. The feed includes an orthomode transducer to generate dual circular polarisation (RHCP and LHCP). TMS-L2 antenna can work in transmit and receive mode via a classical diplexer (OMT), whereas TMS-L3 can only receive. The TMS-L2 antenna control system can be operated in local or remotely controlled and provides only position-preset mode. The antenna can be slaved to TMS-6 by means of locally developed software, supporting program track and autotrack modes. TMS-L3 is not equipped with any antenna control unit and therefore can only be moved by hand.

Description

There are two independent transmit chains to generate signal in each polarisation, or to combine two signals in one polarisation only. The antenna shelter is equipped with two R&S SMHU signals generators. The received signals, separated from transmitted signal by a diplexer, are presented to the LHC and RHC antenna inputs and then delivered to the first stage of the LNA’s via isolators.

- 45 -


R & S Z4 -63 to +13 dBm-16 to -56 dBm

R & S Z4 -63 to +13 dBm0 to 60 dBm

OMT

HPA2

HPA1

+

SW11104

SW16105

SW17106

HEAD B

C13

- 30 dB

SW18107

Note:

All switches but S40 and S41 are shown in default position. The S40 and S41 are floating until energized.

Downconverter does not exist in shelter.

Diameter: 2.4 m Assumed antenna gain (at TX/RX interfaces): - TX: 29.3 dBi @ 1.6435 GHz - RX: 29.0 dBi @ 1.5445 GHz Maximum EIRP: 47 dBW G/T: 7.0 dB/K

SW1100

dBW

dBW/m2

-30 dB

204

205

206

SW2101

- 30 dB

Dual 50 Mhz REFERENCE

PILOT HEAD

IBM Compatible

TX PM

IEEE ADDR 1CH

A

C11

A14

C14

C30 A16

C18

J6RX2

J7 Pilot0 dBm

B16-20 dB

B18B19

B23

SW4102

200J5

RX1

J11

SW8103

C23

C19

C25

C24

C20

-30 dB

LAN

IEEE

C12

A15

CH

B

ACUIEEE ADDR 8

HP 3488AIEEE ADDR 4

1

2

3

-3 dB -3 dB

-36 dB

D10

B28

B17

B27

J57

J56

-36 dB

C26

C28

C27

C29

J4

J9 J5

J6

To TMR

J3

J2

SHELTERPLATFORM

10 to 50 dBm

10 to 50 dBm

Synthesizer 1R & S SMHUIEEE ADDR 5 Tx1

Up

Converter

Synthesizer 2R & S SMHUIEEE ADDR 6 Tx2

Up

Converter

AWG 2021IEEE ADDR 10

HP8594ESpect. Analyser

IEEE ADDR 9 Tx1/2

NRV-Z4

IN

SWEEP

13 dBm Rx

0 dBm Tx

13 dBm U/C

0 dBm Tx

3 dBm

0 dBm

J4LO

J5RF

J270Mhz

J370MHz

J11Mhz

-10 dBm

-10 dBm

BW 10 Khz

14 dB

R & S Z4 -63 to +13 dBm-16 to -56 dBm

HEAD A

J58

C2

C3

C1

C4

C5

C23

C7

C6

A7

B2

D3

D4

D5

J13

J12

J1J2

-13 dBm

-13 dBm

RX PM

IEEE ADDR 3

CH BCH A

J8

-60 to 0 dBm

3 dBm

DistributionBox

RX1

RX2

PILOT

TO D/C (RF)

ANALYSER

SOURCE 1

-67 to -7 dBm

-67 to -7 dBm

0 dBm

0 dBm

TO D/C (LO)

PILOT SYNTH

TX SYNTH

TO U/C (LO)

FROM U/C

To TMR

21.4 MHz

- 3 dB

1626 - 1661 MHz

TMS-L2 block diagramFile name: TMS-L2.vsdDrawn by : Serge LUpdated by : Th. DENISRev. date : 21 January 2003

Splitter

LHCP

RHCP

DIPLEXER

J3

J2

201202203

SW40

C17

1

2

3

C8

LNA1

LNA2

Split

ter

Split

terD12

D11

D13

B10

B11

B20

B21

B5

B7

B12

B13

B24

B22

13dB B3

S41

S32

B26

B25

B15

B14

207

208

209

210

S42

300301302303

SW43

304305306307

SW44

1

2

4

3

2

1

3

4

Split

ter

TX2

TX1

2

1

3

4

SplitterSplitter

Splitter

J55Tx RHCP

Rx RHCP

Rx LHCP

Tx LHCP

Pilot

J54

J52

J53

J51

Revision history : TD: 24/10/2001: correction in diplexer polarisation. TD: 23/05/2002: label correction of head power meter. TD: 21/01/2003: added frequency plan.

Frequency plan

Tx : 1626 -> 1661 MHz

Rx : 1530 -> 1559 MHz

Figure 13: TMS-L2 schema

Characteristics

Transmit (TMS-L2): • Transmit frequency bands: 1.626 to 1.661 GHz • Number of simultaneous carriers:

two, one on each polarisation or both on one polarisation after high power combining

• Maximum EIRP: 47 dBW single carrier operation 44 dBW per carrier when combined

• EIRP range: maximum to 40 dB down • EIRP accuracy: ± 0.5 dB over the entire frequency range • SSPA output power: 100 W • HPA C/I3 intercept point: +56.5 dBm • Power measurement accuracy: 0.1 dB • Power versus frequency: ≤ 1 dB over full band ≤ 0.2 dB over any 4 MHz

• AM to PM conversion: 2 deg/dB • Group delay response: ≤ 4 ns over full band • Power stability: ≤ ± 1 dB over 24 hours at 10°C

- 46 -


• Frequency stability: < 1x10-9 over 24 hours after 30 days operation (according to R&S SMHU

specifications) • •SSB Phase noise: < -124 dBc(1Hz) at 2000 MHz and 20 kHz offset(according to R&S SMHU

specifications) • Input VSWR (J8/J9 ports): 1.22:1 • Output VSWR (J2/J3 ports): 1.22:1

Receive:

• Receive frequency band: 1.53 to 1.559 GHz • Overall Gain: 70 dB • Noise figure: 1.4 dB • G/T (clear sky, 30° elevation): > 7 dB/K • Power measurement range: -130 dBm to –60 dBm • Flux measurement accuracy: ± 0.1 dB • Pilot measurement accuracy: ± 0.1 dB • Gain ripple: ± 2 dBpp over full frequency range ± 0.3 dBpp over any 4 MHz • Gain stability: ± 1 dB over 24 hours • Group delay overall: ±7 nspp over full frequency range ±1 nspp over any 4 MHz • C/I3 Intercept. Point: +18 dBm • Input VSWR (J2/J3 ports): 1.17:1 • Output VSWR (J5/J6 ports): 1.17:1

- 47 -


TMS-S

The UHF S-band transportable station, TMS-S, is part of the overall REDU IOT facility. This antenna is capable of simulating the payload of a low orbiting spacecraft. It is connected to the main Payload Test Laboratory (PTL) by low-loss coaxial cables operating directly at the RF frequency.

Antenna

Figure 14: TMS-S Antenna

TMS-S is a parabolic 2.4-metre antenna that can be oriented from 87-273 degrees in Azimuth, -1-74 degrees in elevation. The feed includes an orthomode transducer to generate dual circular polarisation (RHCP and LHCP). The antenna can work in transmit and receive mode via a classical diplexer (OMT). The TMS-S antenna control system can be operated in local or remotely controlled and provides only position-preset mode. The antenna can be slaved to TMS-6 by means of a locally developed software, supporting program track and autotrack modes.

Description

There are two independent transmit chains to generate signal in each polarisation, or to combine two signals in one polarisation only. The received signals, left and right polarisation separated by the orthomode transducer, are presented to the LHC and RHC antenna ports (diplexer’s input) and then delivered to the first stage of the LNA’s via isolators.

- 48 -



• Transmit frequency bands: 2200 to 2290 MHz • SSPA output power: 60 W • Number of simultaneous carriers:

two, one on each polarisation or both on one polarisation after high power combining • Maximum EIRP:

50 dBW single carrier operation 47 dBW per carrier when combined

• EIRP range: maximum to 40 dB down spread over 2 ranges involving one high power attenuator per chain

• HPA C/I3 intercept. point: +54.5 dBm • Gain variation: ≤ 0.5 dBpp over full band ≤ 0.05 dBpp over any 4 MHz • Gain stability: ≤ ± 1 dB over 24 hours at 10°C • AM to PM conversion: 2 deg/dB at –1dB gain compression point • Power measurement accuracy: 0.1 dB • Input VSWR (J8/J9 ports): 1.17:1 • Output VSWR (J2/J3 ports): 1.17:1

Receive:

• Receive frequency band: 2025 to 2110 MHz • Overall Gain: 75 dB • Noise figure: 1.4 dB • G/T (clear sky, 30° elevation): > 9 dB/K • Power measurement range: -130 dBm to –60 dBm • Flux measurement accuracy: ± 0.1 dB • Pilot measurement accuracy: ± 0.1 dB • Gain ripple:

± 2 dBpp over full frequency range ± 0.3 dBpp over any 4 MHz

• Gain stability: ± 1 dB over 24 hours • Group delay overall:

± 7 nspp over full frequency range ± 1 nspp over any 4 MHz

• C/I3 intercept point: +21 dBm • Input VSWR (J2/J3 ports): 1.17:1 • Output VSWR (J5/J6 ports): 1.17:1

- 49 -


R & S Z4 -63 to +13 dBm-16 to -56 dBm

R & S Z4 -63 to +13 dBm-16 to -56 dBm

R & S Z4 -63 to +13 dBm0 to 60 dBm

HPA2

HPA1

SW11104

SW16105

SW17106

HEAD B

C13

- 30 dB

SW18107

Note:

All switches but S40 and S41 are shown in default position.The S40 and S41 are floating until energized

Diameter: 2.4 mAssumed antenna gain (at TX/RX interfaces): - TX: 32.0 dBi @ 2.25 GHz - RX: 31.4 dBi @ 2.07 GHzMaximum EIRP: 50 dBWG/T: 9.0 dB/K

SW1100

dBW

dBW/m2

-30 dB

SW2101

- 30 dB

Dua

l 50

Mhz

R

EFER

ENC

E

HEAD A

PILOT HEAD

IBM Compatible

TX PM

IEEE ADDR 1

RX PM

IEEE ADDR 3

CH

A

CH BCH A

C11

A14

C14

C30A16

C18

C17

J6RX2

J7 Pilot

3 dBm

B16-20 dB

B18B19

B23

SW4102

J5RX1

J11

SW8103

J13

C23

C19

C25

C24

C20

-30 dB

J12

LAN

IEEE

C12

A15

CH

B

ACUIEEE ADDR 8

HP 3488AIEEE ADDR 4

SW19108

SW21109

C29

C28

20 dB

20 dB

-3 dB -3 dB

-10 dB

B28

B17

B27

2025 - 2110 Ghz

J57

J58

J56

-10 dB

C26

C28

C27

C29

J8 J4

J9 J5

J3

J2

J1

J7

J6

J5

J3

J2 -44.5 to -4.5 dBm

-44.5 to -4.5 dBm

-46.8 to -6.8 dBm

-46.8 to -6.8 dBm

-59.5 to -4.5 dBm

-59.5 to -4.5 dBm

-46.5 to 2.5 dBm

2025 - 2110 Ghz

2025 - 2110 Ghz

2200 - 2290 Ghz

2200 - 2290 Ghz

-57 to -2 dBm

-57 to -2 dBm

-49 to 0 dBm

SHELTERPLATFORM

10 to 50 dBm

2200 - 2290 Ghz

10 to 50 dBm

2200 - 2290 Ghz

201202203

SW40

12

3

TMS-S block diagramFile name : TMS-S.vsdDrawn by : Serge LUpdated by : Thibault DRev. date : 24 March 2003

OMT

J55

Splitter

LHCP

RHCP

DIPLEXER

Tx RHCP

Rx RHCP

Rx LHCP

Tx LHCP

Pilot

J54

J52

J53

J51

J3

J2

204

205

206

200

1

2

3

D10

LNA1

LNA2

Split

ter

Split

terD12

D11

D13

B10

B11

B20

B21

B5

B7

B12

B13

B24

B22

13dB B3

S41

S32

B26

B25

B15

B14

Frequency plan

Tx : 2.2 -> 2.29 GHz

Rx : 2.025 -> 2.11 GHz

Revision history :

TD: 21/01/2003: added antenna specificationTD: 24/03/2003: value of C23 & C24 have been corrected

Reference points

C 23

Figure 15 : TMS-S Schema

- 50 -


TMS-Ka

The Ka-band station, TMS-Ka, is part of the overall REDU IOT facility and was designed in the frame of the ARTEMIS project. The frequency bands were tailored to simulate a Ka-Band LEO user spacecraft for the data relay payload of ARTEMIS. The station is connected to the main Payload Test Laboratory (PTL) by low-loss coaxial cables operating at an intermediate frequency centred on 750 MHz.

Antenna

Figure 16 : TMS-Ka Antenna

The TMS-Ka antenna is a dual offset 1.8-metres parabolic reflector. The feed horn and the aluminium subreflector are installed on a specific support. The antenna is circularly polarised and has four ports: two receive ports (LHCP and RHCP) and two transmit ports (LHCP and RHCP). The receive antenna gain at 23.33 GHz is 50.9 dBi and the transmit gain at 26.41 GHz is 51.8 dBi. The structure of the antenna pedestal allows an azimuth angle range of 105-255 degrees and an elevation range of 1-70 degrees. The TMS-Ka antenna can be operated in local using the user interface or remotely controlled via IEEE-488 interface bus. The system has four operation modes: preset, program track, speed control and stand-by. The antenna can be slaved to TMS-6 antenna by means of a locally developed software.

Description The TMS-Ka transmit system consists of two independent and identical transmit chains able to generate signals in each polarisation or to be combined in one polarisation only. A TX auxiliary down-converter is also part of the transmit subsystem. The two receive chains

- 51 -


consist of a LNA, down-converter and gain/frequency response equaliser. An HP-UX workstation is located in the antenna shelter. This computer controls and monitors all the station equipment via HP-IB buses.


• Transmit frequency band: 25250-27500 MHz • Instantaneous bandwidth: 250 MHz • Frequency stability: 1.0e-9 per day (R&S SMGU synthesiser) • Number of simultaneous carriers: two, one on each polarisation or both on one polarisation after high power combining • TWTA max. output power: 40W • EIRP range: maximum to 60 dB down spread over 2 ranges involving one 17.5dB high power

attenuator • EIRP control: ALC loop or fixed-gain • EIRP accuracy: ≤0.4 dB RSS • EIRP stability: ≤ 0.2 dB/24h (ALC mode) • Transmit chain gain flatness :

TX1 : < 5 dB over the whole SHF band TX2 : < 3.7 dB over the whole SHF band

• TWT Gain flatness : < 1 dB in any 250MHz band • AM/PM conversion2: < 6°/dB • Third order Intermodulation2: ≤-29 dBc, 2 carriers at 10MHz, 10 dB O.B.O. • Group delay: ≤ 4 nspp in any 250 MHz band • Phase noise:

-42 dBc/Hz at 10 Hz -65 dBc/Hz at 100Hz -90 dBc/Hz at 1kHz -98 dBc/Hz at 10kHz

Receive:

• Receive frequency band: 23120-23550 MHz • Instantaneous bandwidth: 250 MHz • G/T (clear sky, 30° elevation): 23 dB/K • Flux measurement range: -90 to –130 dBW/m² • Flux measurement accuracy: ≤0.4 dB RSS • Pilot measurement accuracy: ≤0.14 dB (R&S power meter spec.) • Gain flatness at 750 MHz interf.: 1 dBpp • Gain stability: 0.33 dB over 24 hours • Group delay at 750 MHz interf.: 1.35 nspp • AM to PM conversion: ± 1°/dB • Third order intermodulation: ≤-40 dBc, 2 carriers at 10MHz

- 52 -


• Frequency stability: 1.0e-9 per day (R&S SMGU synthesiser) • Phase noise:

-35 dBc/Hz at 10 Hz -73 dBc/Hz at 100 Hz -78 dBc/Hz at 1 kHz -91 dBc/Hz at 10 kHz

DIPLEXER

LNA1

L

TMS-Ka block diagramFile name:TMS-Ka.vsd

Drawn by S. LedouxModified by Th. DENISrev. date 24/03/2003

23.15 / 23.55 GHz

X 5 X 4

HPA2

HPA1

AM X 2

X 5 X 4

X 5 X 4

X 10 PILOT SYNTHESISERLevel +14 dBm

RX SYNTHESISERLevel +16 dBm

TX SYNTHESISERLevel +14 dBm

NRV Z6

NRV Z6

NRV Z6

L

R

R

30

30

S30

30

40

40

40

40 20

20

RACK A REAR PANELRF FRONT-END CABLES EQUIPMENT RACK A

LNA2

S17

S21

S1

S19

S23

S16

S32

PILOT TX7

ALC only

ALC only

17.5

17.5

180

AUX. in

-3 dBm

A

B

LO-MON. LO-MON.

750 nom. -20 dBm RX 1

RX 2

+10 dBm1118.5 / 1140 MHz

TO RX LO.

TO PILOT

AM

AUX. OUT

TX 1

TO TX 2 LO.( A200 )

2 dBm

+12 dBm

-14 dBm

-20 dBm

750 MHz

750 MHz

1156 / 1177.5 MHz

750 nom. -20 dBm

TO TX 1-LO( A300 )

TX 2

2 dBm

-20 dBm

750 MHz

A300

A200

X24 1020.63 / 1114.56 MHz

750 MHz

750 MHz

NOM. -20 dBm

NOM. -20 dBm

+16 dBm

COMNO

TX FILTER

POWER DIVIDER3dB

COAX TRANSFERT SWITCH

6 dB

6 dB

50 Ω

10 dB

IF SUBSYSTEM A1200

COAX SWITCH S31

NC

GAIN EQUALIZER

GAIN EQUALIZER

J1

J2

J3

J4

S18

25.25 / 27.54 GHz

Diameter: 1.8 m dual offset

Assumed antenna gain (at TX/RX interfaces): - TX: 50.9 dBi @ 26.41 GHz - RX: 51.8 dBi @ 23.33 GHz

Nominal EIRP: 54 dBWMaximum EIRP: 68 dBW

Nominal IPFD : -100 dBW/m²Maximum IPFD : -93 dBW/m²

G/T: 23 dB/K

Frequency plan

Tx : 25.25 -> 27.54 GHz

Rx : 23.12 -> 23.55 GHz

Revision HistoryTD: 21/01/2003 : switch 30 position has been corrected.TD: 24/03/2003 : switch 23 position has been corrected.

Figure 17: TMS-Ka schema

Payload Test Laboratory The Payload Test Laboratory (PTL) provides the interface to the IOT and ESVA facilities and is the location where IOT and ESVA operations are carried out. The room is mainly equipped with computer consoles. A full set of instruments complete the IOT capabilities deployed in Redu.

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APPENDIX D ARTEMIS FILINGS

ARTEMIS-21.5E-DR

This filing covers: • TT&C links in S-band • Feeder links and TT&C nominal links in Ka-band • Ka-band intersatellite links for data relay function • S-band intersatellite links for data relay functions

TT&C links in S-band

Uplink: 500 kHz centred around 2026.754 MHz. Earth station: any Estrack station or station with similar parameters Downlink: 500 kHz centred around 2201 MHz. Earth station: any Estrack station or station with similar parameters

Feeder links and TT&C nominal links in Ka-band

a) Feeder Up-link (29-30 GHz)

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b) Down-link transponder plan (18-20 GHz)

AR11/C/2507

Frequency GHz

Carrier Type Comms Comms Comms Comms Comms Comms CommsAssigned Frequency Band kHz 100000 100000 100000 100000 100000 100000 100000Carrier designation 6M00G7DDC 2M00G7DBT 1M00G7DBT 10M0G7DBT 6M00G7DDC 2M00G7DBT 100KG7DBTFilter Bandwidth kHz 6000 2000 1000 10000 6000 2000 100Max power dBWMax peak power dBW 18.4 22 15.2 20.1 8.4 12 5.2Max power density dBW/Hz -‐46.4 -‐38 -‐44.8 -‐49.9 -‐56.4 -‐48 -‐54.8Min Power dBW 15.4 19 12.2 17.1 5.4 9 2.2Min power density dBW/Hz -‐49.4 -‐41 -‐47.8 -‐52.9 -‐59.4 -‐51 -‐57.8Satellite Beam Designation FDU FDU FDU FDU FDU FDU FDUSatellite Antenna gain dBi 40.1 40.1 40.1 40.1 40.1 40.1 40.1ES Name TERM1 TERM1 TERM1 TERM2 TERM2 TERM2 TERM2ES antenna gain dB 57.6 57.6 57.6 67.6 67.6 67.6 67.6ES pattern Rec. 465 Rec. 465 Rec. 465 Rec. 465 Rec. 465 Rec. 465 Rec. 465Polarization Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 degTnoise K 1305 1305 1305 1305 1305 1305 1305C/Nreq dB 16.8 16.7 16.6 16.8 16.7 16.6 16.5

C/Ireq dB 29 28.9 28.8 29 28.9 28.8 28.7

ES location Redu Redu Redu Redu Redu Redu ReduES location Fucino Fucino Fucino Fucino Fucino Fucino Fucino

28.65, 28.75, 28.85, 28.95, 29.05, 29.15.29.25, 29.35, 29.45, 29.55, 29.65, 29.75

28.65, 28.75, 28.85, 28.95, 29.05, 29.15.29.25, 29.35, 29.45, 29.55, 29.65, 29.75

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Ka-band inter-satellite links for data relay function

Return link (User spacecraft to ARTEMIS direction): satellite to ARTEMIS. 8 ranges of 250 MHz as per table below. Possible channel sizes: 150, 100 and 20 MHz. Forward link (ARTEMIS to User spacecraft direction) : ARTEMIS to satellite. 6 ranges of 60 MHz as per table below. Possible channel sizes: 10, 2 and 1 MHz

Centre freq MHz Bandwidth MHz Centre freq MHz Bandwidth MHz 25600.00000 250 23205.00000 60 25850.00000 250 23265.00000 60 26100.00000 250 23325.00000 60 26350.00000 250 23385.00000 60 26600.00000 250 23445.00000 60 26850.00000 250 23505.00000 60 27100.00000 250 27350.00000 250

RTN link FWD link

AR11/C/2507

Frequency

Carrier Type Comms Comms Comms Comms Comms Comms Comms CommsAssigned Frequency Band 250000 250000 250000 250000 250000 250000 250000 250000Carrier designation 50M0G1DDT 20M0G1DDT 6M00G1DDT 150M0G1DDT 100M0G1DDT 50M0G1DDT 20M0G1DDT 6M00G1DDTFilter Bandwidth 50000 20000 6000 50000 100000 50000 20000 6000Max powerMax peak power 9 9.7 -‐12.9 9.8 9.7 9 9.7 -‐12.9Max power density -‐68 -‐63.3 -‐77.7 -‐72 -‐70.3 -‐68 -‐63.3 -‐77.7Min Power 6 6.7 -‐15.9 6.8 6.7 6 6.7 -‐15.9Min power density -‐71 -‐66.3 -‐80.7 -‐75 -‐73.3 -‐71 -‐66.3 -‐80.7Satellite Beam Designation FDE FDE FDE FDE FDE FDE FDE FDESatellite Antenna gain 40.2 40.2 40.2 40.2 40.2 40.2 40.2 40.2ES Name TERM1 TERM1 TERM1 TERM2 TERM2 TERM2 TERM2 TERM2ES antenna gain 54 54 54 63.9 63.9 63.9 63.9 63.9ES pattern Rec. 465 Rec. 465 Rec. 465 Rec. 465 Rec. 465 Rec. 465 Rec. 465 Rec. 465Polarization Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 deg Linear, 97 degTnoise 484 484 484 484 484 484 484 484C/Nreq 13.8 13.3 25.7 12.4 14.1 13.9 13.3 25.7

C/Ireq 26 25.5 37.9 24.6 26.3 26.1 25.5 37.9

ES location Redu Redu Redu Redu Redu Redu Redu ReduFucino Fucino Fucino Fucino Fucino Fucino Fucino FucinoFrascati Frascati Frascati Frascati Frascati Frascati Frascati Frascati

18.35 -‐ 18.6 -‐ 18.85 -‐ 19.1 -‐ 19.35 -‐ 19.6 18.35 -‐ 18.6 -‐ 18.85 -‐ 19.1 -‐ 19.35 -‐ 19.6

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Beacon: ARTEMIS to satellite. 2 ranges of 500 kHz for a beacon size of 10 kHz

Centre freq (MHz) Bandwidth (kHz) 23540.00000 500 23545.00000 500

S-band intersatellite links for data relay functions

1 channel for return transmission from Envisat: centre freq 2255 MHz, size 6 MHz 1 channel for forward transmission to Envisat: centre freq 2076.48 MHz, size 6 MHz 1 channel for return transmission from ATV: centre freq 2287.5 MHz, size 5 MHz 1 channel for forward transmission to ATV: centre freq 2106.4 MHz, size 6 MHz

ARTEMIS-21.5E-LM

Feeder links

Uplink in Ku-band: Centre frequency 14240 MHz, bandwidth 20 MHz. Note: the channels defined (450 kHz and 1 MHz) are not the ones actually used for the current L-band applications by Telespazio. Downlink in Ku-band: Centre frequency 12740 MHz, bandwidth 20 MHz. Same note as above for the channels actually used on Artemis.

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L-band user links

Four different types of beams (MLA, MLB, MLC, MLE) with different coverage areas. Note: the actual usability of these frequencies is determined by the ORM output.

Uplink Downlink

Beam Centre freq MHz Bandwidth (kHz) Beam Centre freq MHz Bandwidth (kHz) MLA 1633.00000 3000 MLA 1531.50000 3000 MLA 1640.00000 11000 MLA 1538.50000 5500 MLA 1651.50000 10000 MLA 1550.00000 10000 MLA 1658.50000 4000 MLA 1557.00000 4000 MLB 1633.00000 3000 MLB 1531.50000 3000 MLB 1640.00000 11000 MLB 1538.50000 5500 MLB 1651.50000 10000 MLB 1550.00000 10000 MLB 1658.50000 4000 MLC 1633.00000 3000 MLC 1640.00000 11000 MLC 1651.50000 10000 MLC 1658.50000 4000 MLE 1633.00000 3000 MLE 1640.00000 11000 MLE 1651.50000 10000 MLE 1658.50000 4000

ARTEMIS-21.5E-NAV

Feeder links

Uplink in Ku-band: Centre frequency 13875 MHz, bandwidth 4 MHz Downlink in Ku-band: Centre frequency 13875 MHz, bandwidth 4 MHz

Users link

Downlink signal (EGNOS radionavigation): Centre frequency 1575.42 MHz, bandwidth 4 MHz

artemis announcement of opportunity - esa artes a0 - issue 1.0.pdf · reference documentation ......

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