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ESA UNCLASSIFIED – For Official Use
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ESA-TIA-T-AO-0001
Date: 13/04/2016 Issue 2 Rev 1
ARTEMIS Redu Ground Segment Announcement of Opportunity
ESA UNCLASSIFIED – For Official Use
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ESA-TIA-T-AO-0001
Date: 13/04/2016 Issue 2 Rev 1
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
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1 ACRONYMS
AMCF ARTEMIS Mission Control Facility AO Announcement of Opportunity. AOCC ARTEMIS Operations Control Centre ARTEMIS Advanced Data Relay and Technology Mission 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
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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.
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4 INTRODUCTION
This document presents the ESA ARTEMIS Announcement of Opportunity including:
Description of the opportunity Conditions of the ESA ARTEMIS Announcement of Opportunity Selection process Evaluation Criteria Proposal guidelines
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).
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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.
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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).
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Figure 2 : Redu-2 Block Diagram (TMS-1M)
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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.
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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)
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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
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
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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.
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Characteristics Transmit:
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
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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
Prime and backup MAM power meters
Prime and backup MAM power meters
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
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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.
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Characteristics Transmit:
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).
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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
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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.
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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
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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
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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.
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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: +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
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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
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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
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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: 25250-27500 MHz Instantaneous bandwidth: 250 MHz Frequency stability: 1.0e-9 per day (R&S SMGU synthesiser) Number of simultaneous carriers:
two, one on each polarisation or both on one polarisation after high power combining
TWTA max. output power: 40W EIRP range:
maximum to 60 dB down spread over 2 ranges involving one 17.5dB high power attenuator
EIRP control: ALC loop or fixed-gain EIRP accuracy: 0.4 dB RSS EIRP stability: 0.2 dB/24h (ALC mode) Transmit chain gain flatness :
TX1 : < 5 dB over the whole SHF band TX2 : < 3.7 dB over the whole SHF band
TWT Gain flatness : < 1 dB in any 250MHz band AM/PM conversion2: < 6°/dB Third order Intermodulation2: -29 dBc, 2 carriers at 10MHz, 10 dB O.B.O. Group delay: 4 nspp in any 250 MHz band Phase noise:
-42 dBc/Hz at 10 Hz -65 dBc/Hz at 100Hz -90 dBc/Hz at 1kHz -98 dBc/Hz at 10kHz
Receive:
Receive frequency band: 23120-23550 MHz Instantaneous bandwidth: 250 MHz G/T (clear sky, 30° elevation): 23 dB/K Flux measurement range: -90 to –130 dBW/m² Flux measurement accuracy: 0.4 dB RSS Pilot measurement accuracy: 0.14 dB (R&S power meter spec.) Gain flatness at 750 MHz interf.: 1 dBpp Gain stability: 0.33 dB over 24 hours Group delay at 750 MHz interf.: 1.35 nspp AM to PM conversion: 1°/dB
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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
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Figure 15: GPTL-TMR
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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.
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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)
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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.
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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.
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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
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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.
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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
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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.
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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.
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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.
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APPENDIX A NOTICE OF INTENT FORM
SUMMARY PAGE
Name of the Bidder company: Contract manager name: Technical manager name: Mailing address: Mailing address: Tel.: Tel.: Fax: Fax: E-mail: E-mail: Statement of firm intention to submit a proposal signed by an authorised representative of the bidder. Description of the intended use of the ARTEMIS 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.
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