Soyuz ST (Guiana Space Centre)
Inaugural launch on 21 October 2011
FunctionMedium-class launch vehicle to complement the light Vega and heavy Ariane 5
ManufacturerProgress Rocket Space Centre, NPO Lavochkin
Country of originRussia
Size
Height46.2 m (152 ft)
Diameter10.3 m (34 ft)
Mass308 t (303 long tons; 340 short tons)
Stages3
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)[1]: 43 
Associated rockets
FamilySoyuz-2 (R-7)
Launch history
StatusTemporary Suspended
Launch sitesCentre Spatial Guyanais
Total launches27
Success(es)26
Failure(s)0
Partial failure(s)1
First flight21 October 2011 [2]
Last flight10 February 2022
Boosters
No. boosters4 [1]: 21 
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 seconds
Burn time118 seconds
PropellantLOX / kerosene
Core stage
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 seconds
Burn time286 seconds
PropellantLOX / kerosene
Second stage (ST-B)
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)
Powered by1 RD-0124
Maximum thrust297.9 kN (67,000 lbf)
Specific impulse359 seconds
Burn time270 seconds
PropellantLOX / kerosene
Upper stage – Fregat
Height1.5 m (4 ft 11 in)
Diameter3.35 m (11.0 ft)
Empty mass920 kg (2,030 lb)
Gross mass7,558 kg (16,663 lb)
Powered byS5.92
Maximum thrust19.85 kN (4,460 lbf) / 14 kN (3,100 lbf)
Specific impulse332 seconds
Burn timeUp to 1100 seconds (up to 20 starts)
PropellantN2O4 / UDMH
[edit on Wikidata]

Soyuz at the Guiana Space Centre (also known as Soyuz at CSG or Arianespace Soyuz) was a European Space Agency (ESA) programme for operating Soyuz-ST launch vehicles from Centre Spatial Guyanais (CSG), providing medium-size launch capability for Arianespace to complement the light Vega and heavy-lift Ariane 5.[3] The Soyuz vehicle was supplied by the Roscosmos with TsSKB-Progress and NPO Lavochkin, while additional components were supplied by Airbus, Thales Group and RUAG.[1]: 28–30  Autor LV (ICBM) = NPO "Energia", Kaliningrad.

The Arianespace Soyuz project was announced by the ESA in 2002. Cooperation with Russia began in two areas: construction of a launch site for Soyuz in CSG and development of the Soyuz launch vehicle modified for the Guiana Space Centre. A Programme Declaration was signed in 2003 and funding along with final approval was granted on 4 February 2005.[4][5] Initial excavation for the Ensemble de Lancement Soyouz (ELS; Soyuz Launch Complex) began in 2005, construction started in 2007, and the launch complex was completed in early 2011,[6] allowing Arianespace to offer launch services on the modified Soyuz ST-B to its clients.[1][7] Two early flights, VS02 and VS04, and a recent flight, VS17, used the Soyuz ST-A variant.[8][9][10] Since 2011, Arianespace has ordered a total of 23 Soyuz rockets, enough to cover its needs until 2019 at a pace of three to four launches per year.[11][12]: 10  Due to Russia's invasion of Ukraine, Soyuz launches from the Guiana Space Centre have been suspended.[13]

Features of modified Soyuz for the Guiana Space Centre

Vehicle processing

Soyuz components arrived at the CSG via ship, and were unloaded and placed in a storage area. From there, the components were brought to the Launch Vehicle Integration Building where they were assembled horizontally in an air-conditioned environment. First four boosters were attached to the core stage, and then the third stage was attached to the core – identical to the procedure at Baikonur and Plesetsk Cosmodrome. Separately, the payload was mounted on a dispenser in a Payload Processing Facility and then transferred into the S3B building to be mounted to the Fregat upper stage and then encapsulated in a fairing. Subsequently, the first 3 stages of the Soyuz-ST were transported from the Integration Building to the launch pad by a train which also erected the rocket to the vertical position at the pad, where Soyuz was suspended by four support arms. Once vertical, a mobile gantry moved in and enclosed Soyuz. Following that the encapsulated Fregat and payload was lifted vertically by a mobile gantry to be mounted on top of Soyuz. The Mobile Gantry was retracted an hour before the launch.[15][16][17][18][19]

Future developments

Arianespace planned to operate Soyuz until at least the end of 2019, and as of 2014 intended to continue operating Soyuz alongside the planned Ariane 6 when that launcher makes its debut.[11][20] However, the announcement of new Ariane 6 designs from Airbus and Safran opens the possibility of Ariane 6.2 replacing Soyuz.[21] As Ariane 6 flight test slips to 2022,[22] several flights were planned for Soyuz as late as 2022 before the Russians pulled out.

Launch history

Inaugural flight

The first contract for the launch of Soyuz ST-B from Centre Spatial Guyanais (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.[23] The contract for the satellites themselves had already been signed by ESA and Galileo Industries in 2006.[24]

Launch vehicle components shipped from Saint Petersburg first arrived in French Guiana by ship in November 2009.[25] 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.[6][26] The launch site was officially handed over from ESA to the Arianespace on 7 May 2011.[27]

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.[28] 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,[29] making it the first time Soyuz was launched outside of the former Soviet Union territory.[30]

Flight VS09

On 22 August 2014, Arianespace launched the first two Full Operational Capability satellites for the Galileo satellite navigation constellation into medium Earth orbit.[31] 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.[32]

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.[33] 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.[34]

On 25 August 2014, Arianespace announced the creation of an independent inquiry commission to investigate the anomaly.[35] 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.[36]

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".[37][38]

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.[39]

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.[40]

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.[41]

Missions

Date and
time, UTC 		Flight Payload Payload mass Orbit Result No.
21 October 2011,
10:30:00		 VS01 [2] Galileo IOV-1/2 1,580 kg (3,480 lb) MEO Success 1
17 December 2011,
02:03:08		 VS02 [42] Pleiades 1, SSOT, 4 x ELISA 2,191 kg (4,830 lb) SSO Success 2
12 October 2012,
18:15:01		 VS03 [43] Galileo IOV-3/4 1,580 kg (3,480 lb) MEO Success 3
2 December 2012,
02:02:51		 VS04 [44] Pléiades 1B 1,070 kg (2,360 lb) SSO Success 4
25 June 2013,
19:27:03		 VS05 [45] O3b F1 3,204 kg (7,064 lb) MEO Success 5
19 December 2013,
09:12:19		 VS06 [46] Gaia 2,105 kg (4,641 lb) L2 Success 6
3 April 2014,
21:02:26		 VS07 [47] Sentinel-1A 2,272 kg (5,009 lb) SSO Success 7
10 July 2014,
18:55:56		 VS08 [48] O3b F2 3,204 kg (7,064 lb) MEO Success 8
22 August 2014,
12:27:11		 VS09 [31] Galileo FOC FM1/FM2 1,607 kg (3,543 lb) MEO Partial failure [49] 9
18 December 2014,
18:37:00		 VS10 [50] O3b F3 3,184 kg (7,020 lb) MEO Success 10
27 March 2015,
21:46:18		 VS11 [51] Galileo FOC FM3/FM4 1,597 kg (3,521 lb) MEO Success 11
12 September 2015,
02:08:10		 VS12 [52] Galileo FOC FM5/FM6 1,601 kg (3,530 lb) MEO Success 12
17 December 2015,
11:51:56		 VS13 [53] Galileo FOC FM8/FM9 1,603 kg (3,534 lb) MEO Success 13
25 April 2016,
21:02:13		 VS14 [54] Sentinel-1B,[55] MICROSCOPE, 3 CubeSats 3,099 kg (6,832 lb) SSO Success 14
24 May 2016,
08:48:43		 VS15 [56] Galileo FOC FM10/FM11 1,599 kg (3,525 lb) MEO Success 15
28 January 2017,
01:03:34		 VS16 Hispasat 36W-1 3,200 kg (7,100 lb) GTO Success 16
18 May 2017,
11:54:53		 VS17 [57] SES-15 2,302 kg (5,075 lb) GTO Success 17
9 March 2018,
14:10:06		 VS18 [58] O3b F4 3,198 kg (7,050 lb) MEO Success 18
7 November 2018,
03:47:27		 VS19 [59] MetOp-C[60] 4,212 kg (9,286 lb) SSO Success 19
19 December 2018,
16:37:14		 VS20 [61] CSO-1 3,565 kg (7,859 lb) SSO Success 20
27 February 2019,
21:37:00		 VS21 [62] OneWeb F6 1,945.2 kg (4,288 lb) LEO Success 21
4 April 2019,
17:03:37		 VS22 O3b F5 3,177 kg (7,004 lb) MEO Success 22
18 December 2019,
08:54:20		 VS23 CHEOPS, COSMO-SkyMed[63] 3,250 kg (7,170 lb) SSO Success 23
2 December 2020
01:33:28 [64]		 VS24 FalconEye-2 1,190 kg (2,620 lb) SSO Success 24
29 December 2020
16:42:07[65]		 VS25 CSO-2 3,562 kg (7,853 lb) SSO Success 25
5 December 2021
00:19:20[66]		 VS26 Galileo FOC FM23/FM24 1,645 kg (3,627 lb) MEO Success 26
10 February 2022
18:09:37[67]		 VS27 OneWeb F13 5,495 kg (12,114 lb) LEO Success 27
Flights by Mission Result
1
2
3
4
2011
2012
2013
2014
2015
2016
2017
2018
2019
2020
2021
2022

  Success     Failure     Partial Failure   Scheduled  

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

Launch sequence

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.[68] The launch sequence is optimized for each mission, the sequence described here is based on flight VS07 which lifted the Sentinel-1A satellite:[19][69]

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)

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