ARTEMIS Redu Ground Segment Announcement of Opportunityemits.sso.esa.int/emits-doc/ESTEC/News/ewsARTEMIS.… · · 2016-04-21ARTEMIS Redu Ground Segment Announcement of Opportunity

ESA UNCLASSIFIED – For Official Use

Page 1/38

ESA-TIA-T-AO-0001

Date: 13/04/2016 Issue 2 Rev 1

ARTEMIS Redu Ground Segment Announcement of Opportunity


Page 2/38

ESA-TIA-T-AO-0001


Table of contents:

1 ACRONYMS .................................................................................................................................................................. 3

2 REFERENCE DOCUMENTATION ........................................................................................................................... 4

3 BACKGROUND ............................................................................................................................................................ 4

4 INTRODUCTION .......................................................................................................................................................... 5

5 DESCRIPTION OF THE OPPORTUNITY ............................................................................................................... 5

5.1 MAIN PRINCIPLES OF THE OPPORTUNITY ................................................................................................................... 5

6 ARTEMIS REDU GROUND SEGMENT .................................................................................................................. 6

TMS1-M (RED-2) ............................................................................................................................................................. 6TMS-4 ............................................................................................................................................................................... 9TMS-5 ............................................................................................................................................................................. 12TMS-6 ............................................................................................................................................................................. 15TMS-L ............................................................................................................................................................................. 18TMS-S ............................................................................................................................................................................. 21TMS-Ka .......................................................................................................................................................................... 24ESA Earth Terminal and IOT facilities (Redu) ............................................................................................................. 31

7 EXPECTED BENEFIT FOR ESA FROM THIS AO ............................................................................................. 32

8 CONTRACTUAL CONDITIONS ............................................................................................................................. 32

9 SELECTION PROCEDURE AND EVALUATION CRITERIA .......................................................................... 34

9.1 SELECTION PROCEDURE........................................................................................................................................... 349.1.1 Step 1: Notice of Intent .................................................................................................................................... 349.1.2 Step 2: Dialogue phase ................................................................................................................................... 349.1.3 Step 3: Proposal submission ........................................................................................................................... 359.1.4 Step 4: Final selection ..................................................................................................................................... 35

9.2 AO PROCESS SCHEDULE .......................................................................................................................................... 359.3 EVALUATION CRITERIA ........................................................................................................................................... 35

10 PROPOSAL GUIDELINES .................................................................................................................................... 36

10.1 GENERAL TENDER CONDITIONS ........................................................................................................................... 3610.2 PROPOSAL CONTENT ............................................................................................................................................ 36


Page 3/38

ESA-TIA-T-AO-0001


1 ACRONYMS

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


Page 4/38

ESA-TIA-T-AO-0001


2 REFERENCE DOCUMENTATION

TMS-1M Antenna System Manual DTOS-REDU-IOT-MAN-3022-OR TMS-4 IOT Antenna System DTOS-REDU-IOT-MAN-1035-OR TMS-5 IOT Antenna System DOPS-REDU-IOT-MAN-1036-OR TMS-6M IOT Antenna System DTOS-REDU-IOT-MAN-1037-OR TMS-KA IOT Antenna System DOPS-REDU-IOT-MAN-1040-OR TMS-L IOT Antenna System DTOS-REDU-IOT-MAN-1038-OR TMS-S IOT Antenna System DTOS-REDU-IOT-MAN-1039-OR ESA Redu Health, Safety and Security Manual DOPS-REDU-FM-MAN-10001-HSR

3 BACKGROUND

ARTEMIS successfully completed more than 10 years in orbit, since its launch in July 2001. 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 2013. 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 5/38

ESA-TIA-T-AO-0001


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 6/38

ESA-TIA-T-AO-0001


6 ARTEMIS REDU GROUND SEGMENT

TMS1-M (RED-2)

Antenna

Figure 1:Redu 2 13.5m 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 7/38

ESA-TIA-T-AO-0001


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 8/38

ESA-TIA-T-AO-0001


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


Page 9/38

ESA-TIA-T-AO-0001


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 12.75 to 14.5 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 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 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.


Page 10/38

ESA-TIA-T-AO-0001


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)


Page 11/38

ESA-TIA-T-AO-0001


DiplexerX

X

X

Y

YY

HPA1

HPA2

+

20 dB

40 dB

20 dB

40 dB

SW19

SW20

SW16

SW17

SW22

SW21

HP

848

4A

HP

848

4A

30 d

B a

tt.

HP438A

SW5

SW4 SW6H

P8

481

A

HP

848

4A

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 10HP8662

synthesiserH

P8

481

A

HP

848

4A

HP438A

30 dB

C3C4

10 dB

10 dB

10 dB

10 dB

20 dB

C9

C1

C2C6C5

70 dB

70 dB

HP

8481

HP436

HP

8481

HP436

C23

C22 65 dB

65 dB

C21

C20

C19

C18

35 dB

35 dB

10 dB

10 dB

SW13

SW12

SW11

SW10

SW9

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 dB

6 d

B

3 dBm

3 dBm

30 dB

20 dB

20 dB

3 d

B

6 d

B

HP

848

1

HP436

HP

84

81

HP436

3 d

B 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 4 : TMS4 schema


Page 12/38

ESA-TIA-T-AO-0001


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 10.70-12.75 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 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. TMS-5 is equipped with monopulse autotrack capability over the receive frequency range.


Page 13/38

ESA-TIA-T-AO-0001



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


Page 14/38

ESA-TIA-T-AO-0001


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

HP

848

1

HP436

HP

8481

HP436

C19

C18

10 dB

10 dB

SW13

SW12

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

HP

8484

A

HP

8484

A

30 d

B a

tt.

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 dB

40 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 d

B

3 dB

6 dB

15 dBm

20 dB

3 dB

6 dB

3 d

B

14 dBm

20 dB

30 dB

30 dB

HP

8481

HP436H

P84

81HP436

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

SW55

SP4 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 6 : TMS-5 schema


Page 15/38

ESA-TIA-T-AO-0001


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 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.


Page 16/38

ESA-TIA-T-AO-0001



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 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 17/38

ESA-TIA-T-AO-0001


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 8 : TMS-6 Schema

3 dB

DIV

IDE

R

3 d

B3

dB

50dB 50

dB

18.1

-20

.2 G

Hz

20

-20

.2 G

Hz

24.7

dB

W


Page 18/38

ESA-TIA-T-AO-0001


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 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-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 19/38

ESA-TIA-T-AO-0001


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

200

J5RX1

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

J1

J2

-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

Splitte

r

LHCP

RHCP

DIPLEXER

J3

J2

201202203

SW40

C17

1

2

3

C8

LNA1

LNA2

Sp

litte

rS

plit

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

Sp

litter

Sp

litterS

plitter

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 10: 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


Page 20/38

ESA-TIA-T-AO-0001


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


Page 21/38

ESA-TIA-T-AO-0001


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 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 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 22/38

ESA-TIA-T-AO-0001



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


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


Page 23/38

ESA-TIA-T-AO-0001


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

EF

ER

EN

CE

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

Sp

litter

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

Spl

itte

rS

plitt

erD12

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 12 : TMS-S Schema


Page 24/38

ESA-TIA-T-AO-0001


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 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-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 25/38

ESA-TIA-T-AO-0001


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:


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


Page 26/38

ESA-TIA-T-AO-0001


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

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

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 14: TMS-Ka schema


Page 27/38

ESA-TIA-T-AO-0001


Figure 15: GPTL-TMR


Page 28/38

ESA-TIA-T-AO-0001


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 29/38

ESA-TIA-T-AO-0001


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 30/38

ESA-TIA-T-AO-0001


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 31/38

ESA-TIA-T-AO-0001


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 32/38

ESA-TIA-T-AO-0001


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 3rd 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 33/38

ESA-TIA-T-AO-0001


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 3rd 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 34/38

ESA-TIA-T-AO-0001


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

9.1.1 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 9.2.

9.1.2 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 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 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 35/38

ESA-TIA-T-AO-0001


proposal. ESA shall be informed of any discussion/meeting organised between the Bidder and RSS and shall be granted the right to attend.

9.1.3 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).

9.1.4 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 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 3rd 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 17th June 4 Final selection 30th 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 36/38

ESA-TIA-T-AO-0001


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.

10.2 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 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 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.


Page 37/38

ESA-TIA-T-AO-0001


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 38/38

ESA-TIA-T-AO-0001


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 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.

Documents

ARTEMIS Redu Ground Segment Announcement of Opportunityemits.sso.esa.int/emits-doc/ESTEC/News/ewsARTEMIS.… · · 2016-04-21ARTEMIS Redu Ground Segment Announcement of Opportunity