ARTEMIS Redu Ground Segment Announcement of Opportunity

Transcription

1 ARTEMIS Redu Ground Segment Announcement of Opportunity Page 1/38

2 Table of contents: 1 ACRONYMS REFERENCE DOCUMENTATION BACKGROUND INTRODUCTION DESCRIPTION OF THE OPPORTUNITY MAIN PRINCIPLES OF THE OPPORTUNITY ARTEMIS REDU GROUND SEGMENT... 6 TMS1-M (RED-2)... 6 TMS TMS TMS TMS-L TMS-S TMS-Ka ESA Earth Terminal and IOT facilities (Redu) EXPECTED BENEFIT FOR ESA FROM THIS AO CONTRACTUAL CONDITIONS SELECTION PROCEDURE AND EVALUATION CRITERIA SELECTION PROCEDURE Step 1: Notice of Intent Step 2: Dialogue phase Step 3: Proposal submission Step 4: Final selection AO PROCESS SCHEDULE EVALUATION CRITERIA PROPOSAL GUIDELINES GENERAL TENDER CONDITIONS PROPOSAL CONTENT Page 2/38

3 1 ACRONYMS AMCF AO AOCC ARTEMIS ATV EET EGNOS EIRP GHz ICD ICS IOT IOTE M&C SLA SR STDM TBC TBD TC TMS ARTEMIS Mission Control Facility Announcement of Opportunity. ARTEMIS Operations Control Centre Advanced Data Relay and Technology Mission Automated Transfer Vehicle ESA Earth Terminal European Geostationary Navigation Overlay Service Equivalent Isotropically Radiated Power GigaHertz Interface Control Document Interface de Communication Standard In-Orbit Test In-Orbit Test and Experimentation Monitor and Control Service Level Agreement Elementary Services Request Spacecraft Trajectory Data Message To Be Confirmed To Be Defined Telecommand Test and Monitoring Stations Page 3/38

4 2 REFERENCE DOCUMENTATION TMS-1M Antenna System Manual TMS-4 IOT Antenna System TMS-5 IOT Antenna System TMS-6M IOT Antenna System TMS-KA IOT Antenna System TMS-L IOT Antenna System TMS-S IOT Antenna System ESA Redu Health, Safety and Security Manual DTOS-REDU-IOT-MAN-3022-OR DTOS-REDU-IOT-MAN-1035-OR DOPS-REDU-IOT-MAN-1036-OR DTOS-REDU-IOT-MAN-1037-OR DOPS-REDU-IOT-MAN-1040-OR DTOS-REDU-IOT-MAN-1038-OR DTOS-REDU-IOT-MAN-1039-OR DOPS-REDU-FM-MAN HSR 3 BACKGROUND ARTEMIS successfully completed more than 10 years in orbit, since its launch in July Since July 2011, the ARTEMIS mission was extended beyond its design lifetime on a best effort basis in the attempt to satisfy the operational needs of the users until March A mission completion plan was 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 issued an 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. Following the European satellite Operators answers to the Announcement of Opportunity issued in 2012, ESA selected AVANTI Ltd and the 2 parties reached an agreement for the transfer of ARTEMIS satellite after the end of ATV-5 Mission. Then since February 2015, AVANTI Ltd owns the ARTEMIS satellite. The ARTEMIS Redu ground infrastructure in Redu Centre is still owned by ESA and it will be maintained till 31/12/2016. To support European industry ESA has decided to open an Announcement of Opportunity to further use this infrastructure after 31/12/2016 considering that the ownership will stay with ESA and the selected Operator will take full responsibility in maintenance and operations. Page 4/38

5 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 The appendix A provides the Bidders the information regarding the template for Notice of intent. 5 DESCRIPTION OF THE OPPORTUNITY 5.1 Main principles of the opportunity This Announcement provides an opportunity for a European Operator to operate the ARTEMIS Redu ground segment in ESA Redu Centre in Redu (Belgium). In return the Operator shall offer a concrete plan that will support/generate activities benefiting the European Space Telecom Industry and the Agency. It is therefore left to the Bidders to define and propose the nature of these activities. The selected Operator will become solely responsible for the maintenance and operations of the ARTEMIS Redu ground segment. The selected Operator shall assume full responsibility for liabilities arising from the operations. ESA will be entitled to invoice for the full costs encountered for operating the ARTEMIS Redu ground segment (e.g. electricity). Page 5/38

6 6 ARTEMIS REDU GROUND SEGMENT TMS1-M (RED-2) Antenna Figure 1:Redu m antenna (TMS-1M) The Redu 2 (TMS-1M) is a 13.5 m Ka-band full geostationary arc capability and is part of the EET facility, which simultaneously supports Data relay, ARTEMIS commanding, telemetry 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, the test equipment s (BER, Spectrum Analyser, Pilot Frequency Counter) EET Data Patch and the M&C computer. Page 6/38

7 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). Page 7/38

8 Figure 2 : Redu-2 Block Diagram (TMS-1M) Page 8/38

9 TMS-4 TMS-4 measures the performance of geostationary satellites in the Ku-Band, with the support of the 9.3 m antenna, which can transmit in dual linear polarisation from to 14.5 GHz; in addition, it is able to receive the to GHz range, also in dual linear polarisation (X and Y). TMS-4 is remotely controlled from the Test Monitoring Room (TMR). Antenna Figure 3: 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 GHz and of 61.7 dbi at interface TX IOT point at 14.5 GHz. The pointing range is 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 uplink to the satellite. Page 9/38

10 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: GHz and in TX/RX mode, using up-converters 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 ( /day) Receive: Receive frequency band: 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 ( /day) Page 10/38

11 Frequency plan TMR interface Tx : Rx : Tx only mode : > GHz Tx / Rx mode : > GHz > GHz > GHz TBD dbm C1 70 db LNA1 Gain = 50 db T = 70 K O/P IP = 20 dbm C3 10 db 10 db C4 TBD dbm Down-conv. 1 A707 HP8662 X 10 synthesiser 750 MHz -23 dbm Diameter: 9.3 m Assumed antenna gain (at TX/RX interfaces): - TX: GHz - RX: GHz Maximum EIRP: 84 dbw G/T: 31.0 db/k 84 dbw Y SW31 X Y X Y Diplexer Y X SW30 SW32 TBD dbm SW7 C2 70 db x 10 C9 20 db SW4 A HP8484A SW5 30 db att. HP8484A SW6 B LNA2 C5 10 db SW25 C6 TBD dbm 10 db HP8592A Spectrum Analyser Down-conv MHz -24 dbm OMT Polariser Test translator HP438A A dbw/m2 X SW33 SW1 DL1 SW2 HP8662 synthesiser A705 SW3b SGH SP4 a 14 dbm SW13 B TBD dbm DL2 SW12 30 db HP8481A HP8484A A TBD dbm C23 65 db C18 35 db C21 10 db SW11 C19 14 dbm SW9 10 db SW10 30 db SW8 HP8481A HP8484A B A HP438A A702 TBD dbm TBD dbm HP438A A701 Hpib bus History rev GK: 29-Aug-2002 : Pin mod config + switch 55 A : t4hpiba B : t4hpibb C22 65 db 35 db C20 SW20 40 db C25 SW22 C27 40 db SW19 SW21 SW3 20 db C24 C26 20 db SW18 SW16 SW17 C16 20 db SP2 + a SP1 6 db C17 20 db C14 a b 3 db C15 6 db 30 db SW23 30 db 3 db b 35 db C11 SP3 40 db C13 35 db C12 40 db C10 3 db 3 dbm SW36 b SW34 SW35 SP5 3 db SW38 HP8481 HP436 HP436 B714 B714 Prime and backup MAM power meters a b HPA1 500W TWTA HPA2 500W TWTA 3 dbm SW40 SW42 SW37 SW39 ALC unit ALC unit HP8481 HP8481 Pin att Pin att SW41 SW43 SW28 3 dbm SW53 SW29 HP436 HP436 B715 B715 Prime and backup MAM power meters HP8481 PIN att/mod T 6 db AM demodulated SW54 tone HP8566B 21.4 MHz Spectrum Analyser SW55 3 db B718 AM Splitter SHF synt 1 SP6 Modulation tone SMP-02 Splitter PM SP7 750 MHz Up-conv. 1 HP8662 X 14 synthesiser A706 Auxilliary 750 MHz down-conv. 750 MHz Up-conv. 2 B719 AM SHF synth 2 SMP-02 PM TMS4 block diagram File name: TMS4.vsd Updated: GK rev. 29/08/2002 Figure 4 : TMS4 schema Page 11/38

12 TMS-5 The 9.3 m antenna can transmit in dual circular or dual circular polarisation over the 17.3 to 18.4 GHz band; in addition it can receive in dual circular or dual linear polarisation in the GHz band. Antenna Figure 5 : TMS-5 antenna TMS-5 has a Cassegrain 9.3 m antenna with a 92cm sub-reflector. It has a gain at interface RX IOT point of 58.8 dbi at GHz and of 61.3 dbi at interface TX IOT point at 17.5 GHz. The pointing range is 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 uplink 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. TMS-5 is equipped with monopulse autotrack capability over the receive frequency range. Page 12/38

13 Characteristics Transmit: Transmit frequency bands: GHz (Linear Pol.) 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: 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 Page 13/38

14 R&S NRV-Z52-30/+20 dbm R&S NRV-Z6-60/+13 dbm R&S NRV-Z52-30/+20 dbm R&S NRV-Z6-60/+13 dbm Frequency plan Tx : > GHz Rx : > GHz -67 dbm C1 53 db - 68 dbm LNA1-18 dbm - 21 dbm C3 10 db C4 10 db SP8 Splitter SW50 For G=62db LO D/C 1 C/I=55 0 dbm O/P R&S SMP02 for 2 carriers A711 3rd IP=27.8 dbm TBC 140 MHz Down-conv. 1 Frequency IF: 140 MHz converter 1 S726/727 TMR interface 750 MHz GPTL RX1-37 dbm Diameter: 9.3 m Assumed antenna gain (at TX/RX interfaces): - GTx: GHz - GRx: GHz Maximum EIRP: 84 dbw G/T: 34 db/k X-L SW41 3 db hybrid SW42 Y-R C2 53 db + 30 db SW14 Gain = 50 db T = 70 K O/P IP = 20 dbm LNA2 Rx Amp OUT Rx OUT C5 10 db C6 10 db SP9 Splitter SW38 SP10 3 db splitter SW51 SP11 R&S SMG 3 db synthesiser splitter 610 MHz A707 Down-conv. 2 Frequency IF: 140 MHz 140 MHz converter 2 S728/729 Low IF SW MHz -34 dbm GPTL RX2-38 dbm 84 dbw -113 dbw/ m2 SGH DL1 20.6dBW OMT Trk coupler Polariser Diplexer Y-R X-L 3 db hybrid SW39 SW1 DL2 L R SW40 SW2 SW43 Trk LNA3 TLT module TLT C9-37 dbm 20 db SW5 Pin AM SW4 SW6 modulator -70/-20 dbm SW7 ps5 PM db GHz 0dBm HP8484A 30 db att. HP8484A ps6 50MHz REF. HP438A B703 SHF synth SMP-02 B705-70/-20 dbm SW25 LO D/C 2 R&S SMP02 A712 R&S FSP spectrum Monitoring LAN analyser A723 R&S FSP spectrum Monitoring LAN analyser A722 Tracking Tracking down-converter receiver ACU VXI???? Switches driver???? C18 10 dbm 10 db SW12 SW13 SW11 50MHz REF. 10 dbm SW10 SW9 SW8 ps4 ps3 R&S NRVD B702 PM2 50MHz REF. ps2 R&S NRVD B701 PM1 ps1 SW 3b C23 60 db C21 40 db C19 10 db - 9 dbm SW3 C22 60 db 40 db C20 SW20 SW19 C15 40 db C14 20 db SW22 SW18 + SW16 SP1 C16 20 db SP2 a 6 db C14 3 db 30 db b SP4 3 db 35 db a 15 dbm b C10 40 db SW23 SW56 SW55 HP8481 HP436 HP436 B714 MAM714 Prime and backup MAM power meters C11 HPA1 300W TWTA ALC unit ALC unit SW58 SW57 Pin att HP dbm SW36 SW53 PIN att/mod AM demodulated SW54 tone B724 HP8566B 21.4 MHz Spectrum Analyser -13 dbm B718 SP 6 9 db 10dBm synth nom. level SW55 AM Splitter SHF synt 1 Modulation tone SMP-02 PM Splitter SP 7 GPTL TX1-15 dbm -4 dbm Up-conv. 1 LO SW MHz HP8662 X GPTL TX2 synthesiser T MHz A706 2dB Auxilliary down-conv. C17 40 db SW21 C16 20 db SW17 C25 SP3 3 db a b 20 db 30 db SP5 35 db 3 db C13 C12 40 db a 14 dbm b SW59 SW60 HPA2 300W TWTA 24.9dBW HP8481 SW62 SW61 Pin att HP dbm SW37-4 dbm Up-conv dbm AM SHF synth 2 T SMP-02 PM 10 db 10dBm synth nom. level B719 SW MHz GPTL Aux. DC Hpib bus A : t5hpiba B : t5hpibb 6 db HP436 HP436 B715 MAM715 Prime and backup MAM power meters Figure 6 : TMS-5 schema TMS5 block diagram File name : TMS5.vsd Rev. date : 27/Sep/2005 Page 14/38

15 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 7: 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 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. Page 15/38

16 Characteristics Transmit: Transmit frequency bands: GHz (at antenna interface) 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 MHz80 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). Page 16/38

17 Receive: Receive frequency band: 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: / day (Redu-1 Cesium oscillator) Phase noise: ref. freq(10mhz)+20*log(n)-4 (N: multiplication factor) dbw DIVIDER 3 db 3 db 50dB 50dB 3 db GHz GHz Figure 8 : TMS-6 Schema Page 17/38

18 TMS-L Two 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 9 : TMS-L antenna Antenna TMS-L2 as well as L3 is a parabolic 2.4-metre antenna that can be oriented from 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-5 or 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. Page 18/38

19 i t PLATFORM SHELTER D10 D11 LNA1 B10 B20 B5 B12 Splitter B24 S B14 J5 RX1 RX1 NRV-Z4 BW 10 Khz 21.4 MHz TO D/C (RF) To TMR -67 to -7 dbm Frequency plan Tx : > 1661 MHz Rx : > 1559 MHz Diameter: 2.4 m Assumed antenna gain (at TX/RX interfaces): - TX: GHz - RX: GHz Maximum EIRP: 47 dbw G/T: 7.0 db/k dbw LHCP J2 OMT J3 dbw/m2 RHCP Splitter J52 Rx LHCP J53 Tx LHCP J51 Pilot J54 Rx RHCP J55 Tx RHCP DIPLEXER MHz C11 C12 C1 A14 SW2 101 SW1 A C13-30 db C2 C14-30 db SW C3 D12 B11 B21 B7 LNA2 D13 B22 13dB B19 B28 B18-3 db -3 db A7 J2 Dual 50 Mhz REFERENCE SW8 103 C6 SW40 3 C C C23 SW11-36 db C C7 C19 C17 C4-30 db SW B13 Splitter S41 B B B26 B3 B27-60 to 0 dbm B16 B17 D3-20 db R & S Z4-63 to +13 dbm 0 to 60 dbm J56 PILOT HEAD SW4 102 B23 B2 D4 R & S Z4-63 to +13 dbm J1-16 to -56 dbm J57 HEAD B D5 R & S Z4-63 to +13 dbm -16 to -56 dbm J58 HEAD A C28 J8 J4 10 to 50 dbm C26 HPA2 J6 RX2 J7 Pilot 0 dbm J11 J13 J12 J3-13 dbm CH A CH B RX PM IEEE ADDR 3 TX PM IEEE ADDR 1 CH B CH A RX2 PILOT 3 dbm TX2-10 dbm Distribution Box S SW Splitter Splitter Splitter Spl ter ANALYSER IN -67 to -7 dbm HP8594E Spect. Analyser J6 IEEE ADDR 9 Tx1/2 SOURCE 1 0 dbm SWEEP ACU IEEE ADDR 8 HP 3488A IEEE ADDR 4 PILOT SYNTH 13 dbm Rx Synthesizer 1 R & S SMHU 0 dbm Tx IEEE ADDR 5 Tx1 TO D/C (LO) 0 dbm TX SYNTH 0 dbm Tx Synthesizer 2 R & S SMHU 13 dbm U/C IEEE ADDR 6 Tx2 TO U/C (LO) J2 J4 70Mhz 3 dbm LO Up J3 70MHz FROM U/C Converter J5 J1 0 dbm RF 1Mhz 14 db C30 SW C5 + C18-3 db A16 C24-36 db C20-30 db C29 J9 C27 10 to 50 dbm J5 HPA1 J2-13 dbm TX1-10 dbm SW AWG 2021 IEEE ADDR 10 LAN IEEE IBM Compatible To TMR 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. 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. Figure 10: TMS-L2 schema TMS-L2 block diagram File name: TMS-L2.vsd Drawn by : Serge L Updated by : Th. DENIS Rev. date : 21 January 2003 Characteristics Transmit (TMS-L2): Transmit frequency bands: to 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: 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 Page 19/38

20 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 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 Page 20/38

21 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 11: TMS-S Antenna TMS-S is a parabolic 2.4-metre antenna that can be oriented from degrees in Azimuth, 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 or TMS-5 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. Page 21/38

22 Characteristics Transmit: 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: 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 Page 22/38

23 3 2 1 Frequency plan D10 D11 PLATFORM B10 B20 B5 B12 SHELTER Tx : 2.2 -> 2.29 GHz Rx : > 2.11 GHz LNA1 Splitter B24 S B14-57 to -2 dbm Ghz J5 RX to -4.5 dbm J5 Diameter: 2.4 m Assumed antenna gain (at TX/RX interfaces): - TX: GHz - RX: GHz Maximum EIRP: 50 dbw G/T: 9.0 db/k D12 LNA2 D13 B11 B22 13dB B21 B7 B13 Splitter S B3 B15 B25 B26 J6-57 to -2 dbm RX Ghz to -4.5 dbm J6 Reference points B27 dbw LHCP J2 J52 Rx LHCP J53 Tx LHCP B19 B18 B16-20 db B17-49 to 0 dbm Ghz J7 Pilot 3 dbm to 2.5 dbm J7 dbw/m2 OMT J3 RHCP C12 Splitter J51 Pilot J54 Rx RHCP J55 Tx RHCP DIPLEXER C11 A14 SW db B28-3 db C17 SW8 103 Dual 50 Mhz REFERENCE SW4 102 B23 J56 J57 R & S Z4-63 to +13 dbm 0 to 60 dbm PILOT HEAD R & S Z4-63 to +13 dbm -16 to -56 dbm HEAD B J11 J13 CH A CH B CH A CH B RX PM IEEE ADDR 3 TX PM IEEE ADDR 1 ACU IEEE ADDR 8 HP 3488A IEEE ADDR 4 SW1 100 A15 SW2 101 C13-30 db C db C23 C25 SW J58 R & S Z4-63 to +13 dbm -16 to -56 dbm HEAD A J12 C14-30 db SW SW SW C28 20 db C19-30 db C28 J8 C26 10 to 50 dbm Ghz J4 HPA to -6.8 dbm Ghz J to -4.5 dbm J3 C18 C30 A16 C24-10 db C29 IEEE IBM Compatible LAN J1 SW SW C20-30 db J9 C27 10 to 50 dbm Ghz J5 HPA to -6.8 dbm Ghz J to -4.5 dbm J2 Note: All switches but S40 and S41 are shown in default position. The S40 and S41 are floating until energized Revision history : TD: 21/01/2003: added antenna specification TD: 24/03/2003: value of C23 & C24 have been corrected C29 20 db TMS-S block diagram File name : TMS-S.vsd Drawn by : Serge L Updated by : Thibault D Rev. date : 24 March 2003 Figure 12 : TMS-S Schema Page 23/38

24 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 13 : 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 GHz is 50.9 dbi and the transmit gain at GHz is 51.8 dbi. The structure of the antenna pedestal allows an azimuth angle range of 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-5 or 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 Page 24/38

25 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. Characteristics Transmit: Transmit frequency band: 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: 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 Page 25/38

26 Third order intermodulation: -40 dbc, 2 carriers at 10MHz 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 Frequency plan RF FRONT-END CABLES RACK A REAR PANEL EQUIPMENT RACK A Tx : > GHz Rx : > GHz Diameter: 1.8 m dual offset Assumed antenna gain (at TX/RX interfaces): - TX: GHz - RX: GHz Nominal EIRP: 54 dbw Maximum EIRP: 68 dbw Nominal IPFD : -100 dbw/m² Maximum IPFD : -93 dbw/m² G/T: 23 db/k / GHz S30 LNA1 LNA2 750 nom. -20 dbm RX dbm LO-MON. LO-MON / 1140 MHz X 5 X nom. -20 dbm TO RX LO. RX 2 GAIN EQUALIZER GAIN EQUALIZER 750 MHz NOM. -20 dbm +16 dbm 750 MHz NOM. -20 dbm RX SYNTHESISER Level +16 dbm L R DIPLEXER A AM X 2 X / MHz TO PILOT AM +12 dbm TX FILTER COAX SWITCH S31 NO COM NC PILOT SYNTHESISER Level +14 dbm L R B NRV Z6 PILOT TX7 IF SUBSYSTEM A1200 AUX. in 750 MHz AUX. OUT 10 db 40 S23-3 dbm -14 dbm 40 S16 A MHz TX 1-20 dbm S19 40 HPA1 20 X 5 X 4 TO TX 2 LO. ( A200 ) 2 dbm db NRV Z6 ALC only S18 POWER DIVIDER 3dB TX SYNTHESISER Level +14 dbm S1 X / MHz 6 db 17.5 NRV Z6 ALC only X 5 X 4 TO TX 1-LO ( A300 ) 2 dbm J3 J1 J4 S32 J2 COAX TRANSFERT SWITCH S S HPA2 A MHz TX 2-20 dbm Revision History TD: 21/01/2003 : switch 30 position has been corrected. TD: 24/03/2003 : switch 23 position has been corrected / GHz TMS-Ka block diagram File name:tms-ka.vsd Drawn by S. Ledoux Modified by Th. DENIS rev. date 24/03/2003 Figure 14: TMS-Ka schema Page 26/38

27 Figure 15: GPTL-TMR Page 27/38

28 Payload Test Laboratory The Payload Test Laboratory (PTL) provides the interface to the IOT and ESVA facilities and is the location where IOT operations are carried out. The room is mainly equipped with computer consoles. Page 28/38

29 A non-exhaustive list of the test that could be performed is: > Beacon EIRP/FREQ. Assesses the beacon EIRP and frequency in orbit with Doppler compensation > C/I3 (third order intermodulation products) Measures the impairment of fidelity resulting from the production of frequencies that are the sum of, and the difference between, frequencies contained in the applied waveform when the S/C TWT is operated in the non-linear mode. > Doppler shift. Measurement of frequency change to the applied carrier due to the motion of the satellite > Flux/Eirp (EIRP/IPFD) Measures the saturation characteristics of the channel in terms of Input Power Flux Density (IPFD) and downlink EIRP, from which the gain of the channel can be inferred. > Gain Adjust Repetitive measurement of Flux/Eirp at differing satellite gains. > Gain transfer (AM/AM characteristics) Measurements of input power to output power variations in the S/C TWT around saturation (Pin/Pout in FGM mode) > ALC response Measurements of input power to output power variation (Pin/Pout in ALC mode) > G/T Measurement of the satellite receives characteristic figure of merit gain to noise temperature. > Gain frequency Measurement of the channel gain to frequency characteristics over the usable bandwidth. > Kp (AM to PM conversion) To measure the change of phase of the applied carrier to an impressed AM modulation as a function of the S/C input backoff measured in /db > Kt (AM to PM transfer) To measure the change of phase of the applied target carrier to an impressed AM modulation source carrier as a function of the S/C input backoff measured in /db > Antenna mapping (MAM) Page 29/38

30 Measures the satellite coverage dependent parameters in orbit i.e.: reconstruct the patterns in orbit > Local Oscillator To measure the S/C translation frequency corrected for Doppler. > Outband Gain frequency Measurement of the channel gain to frequency characteristics outside the usable bandwidth. note: two methods available, one of which can operate while traffic is present. > Spurious output Measurement of unwanted signals usually generated by harmonics in the L.O. > Phase noise Short-term phase stability of the satellite Local Oscillator and down converter chains measured as relative power offsets from the test carrier > XPD Measures the generation of orthogonal components resulting from the S/C antenna polarisation impurity. > Passive Intermodulation Mixing Products (PIMPS) Measures the power of unwanted carriers resulting from the generation of two or more carriers on the satellite transmit antenna which generates a S/C receive frequency which is fed back in the satellite. > Group Delay To measure the distortion that results when the time delay of a signal passing though a device is not constant as a function of frequency In addition to these, there were also all the Earth station testing capabilities and associated specific tools (ESVA), as well additional capabilities (interference monitoring, spectrograms, etc.) A full set of instruments completes the IOT facilities in Redu and this includes also Radiometers. Page 30/38

31 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. Page 31/38

32 7 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 Redu ground segment for experimental/proof of concept or 3 rd parties activities: o Interference mitigation, o IOT, o Etc. Beyond the compensations of the costs encountered by ESA for the operations (eg electricity) the benefits offered to ESA in exchange could not necessary need to take the form of a monetary compensation. However this is not excluded and such compensation will be considered as part of the benefits for ESA. 8 CONTRACTUAL CONDITIONS This section highlights the main legal and contractual principles and requirements 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 Operator of the ARTEMIS Redu ground segment as described in 6. Risk of maintaining and operating ARTEMIS Redu ground segment shall pass to the selected Operator upon signature of the contract with ESA resulting from this Announcement of Opportunity. The Agency offers the ARTEMIS Redu ground segment in the condition as it 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 afterwards due to a possible degradation of the technical condition of the ARTEMIS Redu ground segment, nor for any direct, indirect, incidental or consequential damage such as but not limited to loss of data, profit, frequency licencing and business interruption. The selected Operator shall be liable to pay any fees (eg frequency licencing filling fees) for the usage of the ARTEMIS Redu ground segment. The Agency does not intend to transfer the property of any equipment of the ARTEMIS Redu ground segment as described or to put such equipment at the disposal of the selected Operator in any other way. The selected Operator will take at Page 32/38

33 its own costs the spare parts, instruments, instrument calibration, needed to carry out the operations. It is the selected Operator s responsibility to carry out on his own or to procure or not the operation and maintenance services currently provided through the ARTEMIS ground segment SLA by the incumbent Maintenance and Operation Contractor in Redu RSS. The specific undertakings of the selected Operator shall also be laid down in this contract. The selected Operator may make a proposal for the provisions of services to the incumbent company providing today maintenance and operations for ARTEMIS Redu ground segment (RSS) for its own 3 rd Parties activities if any and to AVANTI Ltd to support ARTEMIS operations if required. In this case, the commercial, financial and legal conditions under which such services would be provided shall be defined between the Operator and the 2 parties. The ESA Frequency Management Office, in cooperation with the selected Operator, will formally request to Belgian authorities any frequency licence required for the purpose of this Contract. The selected Operator is fully responsible for undertaking all the necessary preparatory steps to register the licences needed to operate the ARTEMIS Redu ground segment All the maintenance and operations of ARTEMIS Redu ground segment shall be performed by the selected Operator according to the requirements of the applicable national legislation and following ESA standards and health, safety and security procedures. Page 33/38

34 9 SELECTION PROCEDURE AND EVALUATION CRITERIA 9.1 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 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 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 Step 2: Dialogue phase Additional information regarding the ARTEMIS Redu ground segment 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 possible needed information from RSS aimed at better shaping the Bidder s offer). Questions shall be addressed via 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 RSS, currently in charge of the ARTEMIS ground segment in Redu maintenance and operations, and perform the related due diligence at their cost, if any. In that case, the outcome of this due diligence shall be presented as part of the Page 34/38

35 proposal. ESA shall be informed of any discussion/meeting organised between the Bidder and RSS and shall be granted the right to attend Step 3: Proposal submission By the defined deadline (see calendar in Section 9.2) a full proposal will need to be submitted, with the content defined in Section 10) 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 9.3 will be used to rank the proposals. 9.2 AO process schedule The schedule associated to the AO is defined in the following table: Step Event Date/duration 1 Notice of Intent 29 th April 12h00 (CET ) 2 Technical + Contractual dialogue 29 th April to 3 rd June (A visit of Redu Artemis infrastructure is foreseen week 19 TBC. The date will be communicated to bidders who have submitted a notice of intent). 3 Proposal submission 17 th June 4 Final selection 30 th July Table 1: AO process schedule 9.3 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 Ground Segment Maintenance and Operations and Service provision; 2. Credibility of the operation and maintenance plans of the ARTEMIS Redu ground segment proposed to be executed by the Bidder after taking responsibility; 3. Credibility and benefits for ESA and European Space Telecom Industry to be demonstrated by the Bidder plan of activities. 4. Compliance with ESA contractual and legal conditions. Page 35/38

36 10 PROPOSAL GUIDELINES 10.1 General tender conditions The proposal and all correspondence relating to the present announcement shall be in English. The proposal shall specifically state a period of validity of 6 months from the closing date for the receipt of tenders. Any document submitted in reply to the AO will 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 of the Operator. Expenses incurred in the preparation and dispatch of the proposal will not be reimbursed. This will also include any expenses connected with the dialogue with RSS and to the visits organised by ESA to Redu and participation to meetings, if any. 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 9.2. The template for this document is provided in Appendix A 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 Redu ground segment 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 Redu ground segment and of the proposed activity plan benefiting the European Satellite Telecom Industry; The name, telephone / fax number and 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. Page 36/38

37 2. Detailed description of the intended operations of the ARTEMIS satellite including: Operational & Maintenance 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 RSS or indicate if the operations of the ARTEMIS satellite will be continued with RSS or if the Bidder will take over this role by other means. Intended service duration (at least 5 years+ extensions). 3. Proposal for activities benefiting European Satellite Telecom Industry: The proposal should include concrete evidence of the execution of this plan. 4. Management and contractual proposal including: Industrial organisation (entities and their role); Relevant background information on the entities involved (in particular for satellite ground segment maintenance and operations and service provision). 5. Statement of compliance with the contractual conditions set forth in chapter 8 of the present AO. Page 37/38

38 APPENDIX A NOTICE OF INTENT FORM Name of the Bidder company: SUMMARY PAGE Contract manager name: Technical manager name: Mailing address: Tel.: Fax: Mailing address: Tel.: Fax: Statement of firm intention to submit a proposal signed by an authorised representative of the bidder. Description of the intended use of the ARTEMIS Redu ground segment: If this section is relevant, please include at least: - a description of the service/utilisation of the ARTEMIS Redu ground segment; - the expected duration of the use of ARTEMIS Redu ground segment; - the request to perform the maintenance and operations services; Description of the planned activities benefiting European Space Telecom Industry: Provide as much details as possible on the planned activities. Description of the benefits for the Agency: Indicate if the Bidder is considering providing ATV/EGNOS services. Note: this document should be maximum 10 pages long. Page 38/38