Wikipedia

Soyuz at the Guiana Space Centre

(Redirected from European Soyuz)

Soyuz at the Guiana Space Centre was a European Space Agency (ESA) programme that operated Soyuz-2 launch vehicles at the Guiana Space Centre (CSG). It provided Arianespace with a medium-lift launch vehicle alongside the light-lift Vega and heavy-lift Ariane 5.[4] The rocket was marketed by Starsem a joint venture of ArianeGroup, Arianespace, Progress Rocket Space Centre and Roscosmos.

Soyuz-2 (ST-A / ST-B)
Inaugural launch on 21 October 2011
FunctionMedium-lift launch vehicle
ManufacturerProgress Rocket Space Centre
Country of originRussia
Cost per launchUS$80 million[1]
Size
Height46.2 m (151 ft 7 in)
Diameter10.3 m (33 ft 10 in)
Mass308,000 kg (679,000 lb)
Stages3 or 4
Capacity
Payload to GTO
Mass3,250 kg (7,170 lb)
Payload to GEO
Mass1,440 kg (3,170 lb)
Payload to SSO
Mass4,400 kg (9,700 lb)[2]
Associated rockets
FamilySoyuz-2 (R-7)
Comparable
Launch history
StatusSuspended
Launch sitesGuiana Space Centre, ELS
Total launches27
Success(es)26
Partial failure(s)1
First flight21 October 2011 [3]
Last flight10 February 2022
Type of passengers/cargo
First stage (boosters)
Height19.6 m (64 ft)
Diameter2.68 m (8 ft 10 in)
Empty mass3,784 kg (8,342 lb)
Gross mass44,413 kg (97,914 lb)
Powered by1 × RD-107A
Maximum thrust838.5 kN (188,500 lbf)
Specific impulse262 s (2.57 km/s)
Burn time118 seconds
PropellantLOX / RP-1
Second stage (core)
Height27.1 m (89 ft)
Diameter2.95 m (9 ft 8 in)
Empty mass6,545 kg (14,429 lb)
Gross mass99,765 kg (219,944 lb)
Powered by1 × RD-108A
Maximum thrust792.5 kN (178,200 lbf)
Specific impulse255 s (2.50 km/s)
Burn time286 seconds
PropellantLOX / RP-1
Third stage
Height6.7 m (22 ft)
Diameter2.66 m (8 ft 9 in)
Empty mass2,355 kg (5,192 lb)
Gross mass27,755 kg (61,189 lb)
Propellant mass25,400 kg (56,000 lb)
Powered byA: 1 × RD-0110
B: 1 × RD-0124
Maximum thrustA: 298 kN (67,000 lbf)
B: 294.3 kN (66,200 lbf)
Specific impulseA: 326 s (3.20 km/s)
B: 359 s (3.52 km/s)
Burn time270 seconds
PropellantLOX / RP-1
Upper stage (optional) – Fregat / Fregat-M / Fregat-MT
Height1.5 m (4 ft 11 in)
DiameterFregat / Fregat-M: 3.35 m (11.0 ft)
Fregat-MT: 3.80 m (12.5 ft)
Empty massFregat: 930 kg (2,050 lb)
Fregat-M: 980 kg (2,160 lb)
Fregat-MT: 1,050 kg (2,310 lb)
Propellant massFregat: 5,250 kg (11,570 lb)
Fregat-M: 5,600 kg (12,300 lb)
Fregat-MT: 7,100 kg (15,700 lb)
Powered by1 × S5.92
Maximum thrust19.85 kN (4,460 lbf)
Specific impulse333.2 s (3.268 km/s)
Burn timeUp to 1,100 seconds (up to 20 starts)
PropellantN2O4 / UDMH
[edit on Wikidata]

Launched in 2002, the project involved collaboration with Russia in two key areas: building a launch site at the CSG for Soyuz and modifying the launch vehicle to handle the tropical climate. A formal agreement was signed in 2003, with funding and final approval granted in 2005. Construction of the Ensemble de Lancement Soyouz (ELS; lit. 'Soyuz Launch Complex') began in 2005 and was completed in early 2011.

In its standard configuration, Soyuz-2 is a three-stage launch vehicle designed for low Earth orbit missions. Notably, its stage numbering differs from some rockets. The boosters are considered its the first stage, while the central core is the second. For higher orbits, an optional Fregat upper stage could be added. A total of 27 Soyuz-2 vehicles were launched from the CSG between 2011 and February 2022, with 26 successes and one partial failure (Flight VS09). While most missions at the CSG used the ST-B variant of the Soyuz-2 with a more powerful third stage, nine used the ST-A variant.

Soyuz launches from the CSG were suspended indefinitely in 2022 following Russia's invasion of Ukraine. Additionally, with the introduction of the Vega C and Ariane 6 launchers, both offering medium-lift capabilities, the role previously filled by Soyuz has become largely redundant.

Soyuz modifications for the Guiana Space Centre

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To accommodate the conditions and requirements of the CSG, Soyuz rockets underwent several key modifications. These adaptations ensure the vehicle's optimal performance and safety within the tropical environment.

Launch Infrastructure and Payload Integration

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  • Mobile Service Tower: Unlike other Soyuz launch complexes, the ELS employed a mobile service tower that enabled vertical payload integration directly on the launchpad.[2]
  • European Payload Adapters: Launch vehicles used European-supplied payload adapters, enhancing compatibility with a broader range of spacecraft.[2]
  • Engine Ignition: At the ELS, the engines of the boosters and first stage were pyrotechnically ignited. At other Soyuz launch complexes, engines are chemically ignited.[5]

Enhanced Safety Systems

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  • European Safeguard Kit (French: Kit de Sauvegarde Européenne): This system can locate the rocket in real-time and, if necessary, transmit a flight termination signal, ensuring the safe destruction of the vehicle in the event of an anomaly.[2][5]
  • Destruct System for Boosters and Core Stage: Boosters and core stage are equipped with pyrotechnic devices to ensure they sink in the ocean for disposal after flight.[5]
  • S-Band Telemetry System Adaptation: The S band telemetry system is modified to operate on the Inter-Range Instrumentation Group standard used at the CSG.[2]

Environmental Adaptation

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  • Tropical Climate Adaptation: The air conditioning system is adapted to keep the payload cool inside the faring, and protective measures are added to reduce icing when loading cryogenic fluids in the humid environment.[2]
  • Pest Control: To avoid potential wildlife intrusions, all cavities and openings within the rocket were studied and certified to be adequately sealed against insects and rodents.[5]

Vehicle processing

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Soyuz rockets arrive at the CSG by ship, where components are offloaded and stored for assembly. In preparation for launch, these components are transferred to the temperature-controlled Launch Vehicle Integration (LVI) Building. Here, in a horizontal orientation, the four strap-on boosters are attached to the core stage, followed by the third stage. Several days before launch, a dedicated transporter moves the assembled Soyuz stages from the LVI Building to the launchpad. At the pad, the launch vehicle is erected into a vertical position, and the mobile service tower is moved into place.

Concurrently, within the Payload Processing Facility (PPF) clean room, customer teams prepare their spacecraft. The day before leaving the PPF, the spacecraft is integrated with an adapter/dispenser. This assembly is then transferred to the S3B building, where the fueled Fregat upper stage awaits. Here, the spacecraft and Fregat are integrated and encapsulated within the payload fairing.

Everything comes together on the third day prior to launch when the mobile service tower lifts the encapsulated spacecraft and Fregat upper stage, positioning them atop the Soyuz launch vehicle. Finally, approximately one hour before launch commences, the mobile service tower is meticulously retracted, readying the Soyuz for its mission.[6][7][8][9][10]

Launch history

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Inaugural flight

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The first contract for the launch of Soyuz the CSG was signed at the 2009 Paris Air Show by the Director of the Galileo Programme and Navigation-related Activities René Oosterlinck and a CEO of Arianespace Jean-Yves Le Gall. This contract covered 2 launches of two Galileo satellites each.[11] The contract for the satellites themselves had already been signed by ESA and Galileo Industries in 2006.[12]

Launch vehicle components shipped from Saint Petersburg first arrived in French Guiana by ship in November 2009.[13] The Soyuz Launch Site acceptance review took place during the last week of March 2011, leading to the first simulated launch campaign between 29 April and 4 May 2011.[14][15] The launch site was officially handed over from ESA to the Arianespace on 7 May 2011.[16]

Assembly of the Soyuz ST-B begun on 12 September 2011 in the Assembly and Testing building, while two Galileo satellites underwent final tests after their arrival from Thales Alenia Space facilities in Italy on 7 and 14 September 2011.[17] The launch was planned for 20 October 2011, however an anomaly was detected in the pneumatic system responsible for disconnecting the fuel lines from Soyuz third stage, forcing the mission to be postponed for 24 hours. On 21 October 2011, at 10:30 UTC, Soyuz ST-B took off for its inaugural, 3 hour 49 minute, flight,[18] making it the first time Soyuz was launched outside of the former Soviet Union territory.[19]

Flight VS09

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On 22 August 2014, Arianespace launched the first two Full Operational Capability satellites for the Galileo satellite navigation constellation into medium Earth orbit.[20] The mission appeared to proceed normally and Arianespace reported the launch to be a success, however analysis of telemetry data provided by ESA and CNES tracking stations showed that the satellites were injected into an incorrect orbit.[21]

Orbit Inclination Eccentricity
Targeted 23,222 × 23,222 km 55.0° 0.00
Achieved 25,900 × 13,713 km 49.8° 0.23

The orbit was determined by the European Space Operations Centre within 3 hours after the separation from launcher, and the satellites were operating normally and under control.[22] Both satellites were switched to safe mode, pointing at the sun while both ESA/CNES and OHB teams investigated the failure and options for the satellites.[23]

On 25 August 2014, Arianespace announced the creation of an independent inquiry commission to investigate the anomaly.[24] On 28 August 2014, details emerged on the events that most likely led to a failure of the Fregat upper stage. At the end of the re-orientation phase the flight control system detected an incorrect angular speed and unsuccessfully attempted to use thrusters to correct the situation. The flight control system did not detect the thruster issue and continued the flight plan with the upper stage oriented in a wrong direction, leaving the satellites in an incorrect orbit.[25]

In late September 2014, the Roscosmos commission report, quoted by Izvestia, indicated that the Fregat failure was due to a design flaw leading to freezing in one of the hydrazine propellant lines, which was placed alongside a line carrying cold helium used for pressurization of the main propellant tanks. During the long first burn required for Galileo orbital insertion the propellant line was cooled to below the freezing point of hydrazine. Further investigations were focused on the software error and a means to prevent similar failures in future. Izvestia also reported that the failure of flight VS09 caused a serious reaction in Russian government. Oleg Ostapenko, head of Roscosmos, had a "difficult conversation in the (Moscow) White House".[26][27]

On 7 October 2014, the Independent Inquiry Board announced the conclusions of its investigation, revealing that a proximity of helium and hydrazine feed lines resulted in a thermal bridge that caused an interruption of propellant supply to the thrusters. Ambiguities in the design documents allowing this to happen were a result of not taking into account thermal transfers in the thermal analyses of the stage system design. The Board recommended 3 corrective actions: Revamping thermal analysis, correcting design documents and modification of manufacture, assembly, integration and inspection procedures of the supply lines.[28]

In November 2014, ESA announced the satellites would perform a total of 15 orbital maneuvers to raise their perigee to 17,339 km. This would reduce the satellites' exposure to the Van Allen radiation belt, reduce the doppler effect, increase satellite visibility from the ground, and allow the satellites to keep their antennas pointed at Earth during perigee. These orbits would repeat the same ground track every 20 days, allowing synchronization with other Galileo satellites which repeat the same ground track every 10 days. Once in their new orbits the satellites could begin in-orbit testing.[29]

Recovery of the satellites concluded in March 2015, when Galileo-FOC FM2 entered a new orbit, mirrored to the orbit of Galileo-FOC FM1, which concluded its manoeuvres on the end of November 2014 and successfully passed testing. Currently satellites overfly the same location on the ground every 20 days, comparing to 10 days of standard Galileo satellites.[30]

Missions

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Flight Launch (UTC) Payload Payload mass Orbit Config. Upper Result Ref.
VS01 21 October 2011, 10:30:00 Galileo IOV-1/2 1,580 kg (3,480 lb) MEO Soyuz ST-B Fregat-M Success [3]
VS02 17 December 2011, 02:03:08 Pleiades 1, SSOT, 4 x ELISA 2,191 kg (4,830 lb) SSO Soyuz ST-A Fregat-M Success [31]
VS03 12 October 2012, 18:15:01 Galileo IOV-3/4 1,580 kg (3,480 lb) MEO Soyuz ST-B Fregat-MT Success [32]
VS04 2 December 2012, 02:02:51 Pléiades 1B 1,070 kg (2,360 lb) SSO Soyuz ST-A Fregat Success [33]
VS05 25 June 2013, 19:27:03 O3b F1 3,204 kg (7,064 lb) MEO Soyuz ST-B Fregat-MT Success [34]
VS06 19 December 2013, 09:12:19 Gaia 2,105 kg (4,641 lb) L2 Soyuz ST-B Fregat-MT Success [35]
VS07 3 April 2014, 21:02:26 Sentinel-1A 2,272 kg (5,009 lb) SSO Soyuz ST-A Fregat-M Success [36]
VS08 10 July 2014, 18:55:56 O3b F2 3,204 kg (7,064 lb) MEO Soyuz ST-B Fregat-MT Success [37]
VS09 22 August 2014, 12:27:11 Galileo FOC FM1/FM2 1,607 kg (3,543 lb) MEO Soyuz ST-B Fregat-MT Partial failure [20][38]
VS10 18 December 2014, 18:37:00 O3b F3 3,184 kg (7,020 lb) MEO Soyuz ST-B Fregat-MT Success [39]
VS11 27 March 2015, 21:46:18 Galileo FOC FM3/FM4 1,597 kg (3,521 lb) MEO Soyuz ST-B Fregat-MT Success [40]
VS12 12 September 2015, 02:08:10 Galileo FOC FM5/FM6 1,601 kg (3,530 lb) MEO Soyuz ST-B Fregat-MT Success [41]
VS13 17 December 2015, 11:51:56 Galileo FOC FM8/FM9 1,603 kg (3,534 lb) MEO Soyuz ST-B Fregat-MT Success [42]
VS14 25 April 2016, 21:02:13 Sentinel-1B, MICROSCOPE 3,099 kg (6,832 lb) SSO Soyuz ST-A Fregat-M Success [43][44]
VS15 24 May 2016, 08:48:43 Galileo FOC FM10/FM11 1,599 kg (3,525 lb) MEO Soyuz ST-B Fregat-MT Success [45]
VS16 28 January 2017, 01:03:34 Hispasat 36W-1 3,200 kg (7,100 lb) GTO Soyuz ST-B Fregat-MT Success
VS17 18 May 2017, 11:54:53 SES-15 2,302 kg (5,075 lb) GTO Soyuz ST-A Fregat-M Success [46]
VS18 9 March 2018, 14:10:06 O3b F4 3,198 kg (7,050 lb) MEO Soyuz ST-B Fregat-MT Success [47]
VS19 7 November 2018, 03:47:27 MetOp-C 4,212 kg (9,286 lb) SSO Soyuz ST-B Fregat-M Success [48][49]
VS20 19 December 2018, 16:37:14 CSO-1 3,565 kg (7,859 lb) SSO Soyuz ST-A Fregat-M Success [50]
VS21 27 February 2019, 21:37:00 OneWeb F6 1,945 kg (4,288 lb) LEO Soyuz ST-B Fregat-MT Success [51]
VS22 4 April 2019, 17:03:37 O3b F5 3,177 kg (7,004 lb) MEO Soyuz ST-B Fregat-MT Success
VS23 18 December 2019, 08:54:20 CHEOPS, COSMO-SkyMed 3,250 kg (7,170 lb) SSO Soyuz ST-A Fregat-MT Success [52]
VS24 2 December 2020, 01:33:28 FalconEye-2 1,190 kg (2,620 lb) SSO Soyuz ST-A Fregat-M Success [53]
VS25 29 December 2020, 16:42:07 CSO-2 3,562 kg (7,853 lb) SSO Soyuz ST-A Fregat-M Success [54]
VS26 5 December 2021, 00:19:20 Galileo FOC FM23/FM24 1,645 kg (3,627 lb) MEO Soyuz ST-B Fregat-MT Success [55]
VS27 10 February 2022, 18:09:37 OneWeb F13 5,495 kg (12,114 lb) LEO Soyuz ST-B Fregat-MT Success [56]
Flights by Mission Result
1
2
3
4
2011
2012
2013
2014
2015
2016
2017
2018
2019
2020
2021
2022

  Success     Failure     Partial Failure   Cancelled  

Soyuz launch statistics from Guiana as of July 2019. Source: data from wikitable Missions, wikitable Scheduled flights and Arianespace website.

Launch sequence

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Launch complex with withdrawn mobile gantry

Typically, operations 3 days before launch include countdown rehearsal for all stages as well as final preparations and verification of the Fregat upper stage. Two days before launch preparations for fueling begin. This is also the last day when pre-launch activity with the payload can occur.[57] The launch sequence is optimized for each mission, the sequence described here is based on flight VS07 which lifted the Sentinel-1A satellite:[10][58]

Clock Event Altitude
T− 06:30:00 Mission control team B on a console, beginning of a network countdown
T− 04:50:00 State Commission meeting giving fueling authorization
T− 04:00:00 Beginning of fueling
T− 03:00:00 Payload switched to pre-launch mode
T− 02:20:00 Readiness report
T− 01:45:00 End of fueling
T− 01:21:00 GO / NO-GO roll-call
T− 01:00:00 Mobile gantry withdrawal
T− 00:10:00 Payload switches to onboard power supply
T− 00:06:10 Beginning of autosequence
T− 00:05:00 Fregat switches to onboard power supply
T− 00:01:00 Activation of automatic launch sequence
T− 00:00:40 Launcher switches to onboard power supply
T− 00:00:20 Lower stage umbilical mast withdrawal
T− 00:00:17 Main engine ignition
T− 00:00:15 Preliminary thrust level
T− 00:00:03 Maximum thrust level
T+ 00:00:00 Liftoff
T+ 00:01:11 Max Q
T+ 00:01:58 Boosters separation 60 km (37 mi)
T+ 00:03:29 Fairing separation 120 km (75 mi)
T+ 00:04:47 2nd stage separation 240 km (150 mi)
T+ 00:04:48 2nd stage ignition
T+ 00:04:53 Aft section separation (connects 1st with 2nd stage)
T+ 00:08:46 Fregat upper stage separation
T+ 00:09:46 Fregat ignition 410 km (250 mi)
T+ 00:20:04 Fregat shutdown
T+ 00:23:29 Payload separation 693 km (431 mi)

References

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  2. ^ a b c d e f "Soyuz from the Guiana Space Centre – User's manual" (PDF). Arianespace. March 2012. p. 43. Retrieved 16 December 2015.
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  52. ^ Clark, Stephen (7 April 2017). "Italian radar satellite, European exoplanet telescope to launch on Soyuz next year". Spaceflight Now. Retrieved 8 April 2017.
  53. ^ "Live coverage: Soyuz launches Falcon Eye 2 satellite on third attempt". Spaceflight Now. 1 December 2020. Retrieved 2 December 2020.
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  56. ^ "Arianespace's thirteenth flight for OneWeb successfully deployed 34 additional satellites". Arianespace (Press release). 10 February 2022. Retrieved 11 February 2022.
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