Soyuz-2 (rocket)

Soyuz 2 (Soyuz 2.1a/2.1b/ST-A/ST-B/Soyuz-2.1v)

A MetOp spacecraft ready for the launch atop a Soyuz-2.1a rocket.
Function	Orbital carrier rocket
Manufacturer	TsSKB-Progress
Country of origin	Russia
Size
Height	46.1 m (151 ft)
Diameter	2.95 m (9 ft 8 in)
Mass	305,000 kg (672,000 lb)
Stages	2 or 3
Capacity
Payload to 200 km (110 nmi) circular 51.8° LEO from Baikonur[1]	Soyuz-2.1a: 7,020 kg (15,480 lb) Soyuz-2.1b: 8,200 kg (18,100 lb)
Payload to 820 km (440 nmi) SSO (with Fregat)[2]	Soyuz-2.1a: 4,230 kg (9,330 lb) Soyuz-2.1b: 4,900 kg (10,800 lb)
Payload to 1,500 m/s (4,900 ft/s) deficit GTO (with Fregat from ELS)[2]	Soyuz-2.1a: 2,810 kg (6,190 lb) Soyuz-2.1b: 3,250 kg (7,170 lb)
Associated rockets
Family	R-7 (Soyuz)
Launch history
Status	Active
Launch sites	LC-31/6, Baikonur LC-43, Plesetsk ELS, Centre Spatial Guyanais LC-1S, Vostochny Cosmodrome (future)
Total launches	52 (2.1a: 23, 2.1b: 27, 2.1v: 2)
Successes	47 (2.1a: 21, 2.1b: 25, 2.1v: 1)
Failures	2 (2.1a: 1, 2.1b: 1, 2.1v: 0)
Partial failures	3 (2.1a: 1, 2.1b: 1, 2.1v: 1)
First flight	2.1a: 8 November 2004 2.1b: 27 December 2006 2.1v: 28 December 2013
Notable payloads	COROT, Galileo
Boosters - Blok-B,V,G,D[3]
No boosters	4
Length	19.6 m (64 ft)
Diameter	2.68 m (8.8 ft)
Empty mass	3,784 kg (8,342 lb)
Gross mass	39,160 kg (86,330 lb)
Propellant mass	44,413 kg (97,914 lb)
Engines	RD-107A
Thrust	Sea Level: 839.48 kN (188,720 lbf) Vacuum: 1,019.93 kN (229,290 lbf)
Specific impulse	Sea Level: 263.3 s (2.582 km/s) Vacuum: 320.2 s (3.140 km/s)
Burn time	118 seconds
Fuel	LOX/RG-1
First Stage - Blok-A[3]
Length	27.10 m (88.9 ft)
Diameter	2.95 m (9.7 ft)
Empty mass	6,545 kg (14,429 lb)
Gross mass	99,765 kg (219,944 lb)
Propellant mass	90,100 kg (198,600 lb)
Engines	RD-108A
Thrust	Sea Level: 792.41 kN (178,140 lbf) Vacuum: 921.86 kN (207,240 lbf)
Specific impulse	Sea Level: 257.7 s (2.527 km/s) Vacuum: 320.6 s (3.144 km/s)
Burn time	286 seconds
Fuel	LOX/RG-1
Second Stage - Blok-I[3]
Length	6.70 m (22.0 ft)
Diameter	2.66 m (8.7 ft)
Empty mass	2,355 kg (5,192 lb)
Gross mass	27,755 kg (61,189 lb)
Propellant mass	25,400 kg (56,000 lb)
Engines	Soyuz-2.1a/Soyuz-STA: RD-0110 Soyuz-2.1b/Soyuz-STB: RD-0124
Thrust	RD-0110: 298 kilonewtons (67,000 lbf) RD-0124: 294.3 kilonewtons (66,200 lbf)
Specific impulse	RD-0110: 326 seconds RD-0124: 359 seconds
Burn time	270 seconds
Fuel	LOX/RG-1
Upper Stage (optional) - Fregat-MT[3]
Length	1.5 m (4.9 ft)
Diameter	3.35 m (11.0 ft)
Empty mass	902 kg (1,989 lb)
Propellant mass	6,638 kg (14,634 lb)
Engines	S5.92
Thrust	19.85 kilonewtons (4,460 lbf)
Specific impulse	332 seconds
Burn time	1100 seconds
Fuel	N2O4/UDMH

Soyuz-2, GRAU index 14A14, is the collective designation for the new version of the Russian Soyuz rocket. In its basic form, it is a three-stage carrier rocket for placing payloads into low Earth orbit. The first-stage boosters and two core stages feature uprated engines with improved injection systems, compared to the previous versions of the Soyuz. Digital flight control and telemetry systems allow the rocket to be launched from a fixed launch platform, whereas the launch platforms for earlier Soyuz rockets had to be rotated as the rocket could not perform a roll to change its heading in flight.

Soyuz-2 is often flown with an upper stage, which allows it to lift payloads into higher orbits, such as Molniya and geosynchronous orbits. The upper stage is equipped with independent flight control and telemetry systems from those used in the rest of the rocket. The NPO Lavochkin manufactured Fregat is the most commonly used upper stage.

Soyuz-2 rockets are currently launched from LC-31 at the Baikonur Cosmodrome, and LC-43 at the Plesetsk Cosmodrome, launch facilities shared with earlier R-7 derived rockets including the Soyuz-U and Molniya. Commercial Soyuz-2 flights are contracted by Starsem, and have launched from LC-31 at Baikonur and ELS (l'Ensemble de Lancement Soyouz), which has been built at the Guiana Space Centre on the northern coast of South America. The Soyuz-2 is expected to be able to deliver 2.8-3.5 tonnes to GTO from this site.

The Soyuz-2 has replaced the Molniya-M^[4] and is starting to replace the Soyuz-U and Soyuz-FG rockets which are currently in service alongside it, as they are expected to be phased out from 2014 onwards.^[5][6]

Variants

Soyuz-2 family includes 2.1a, 2.1b and 2.1v. The first two variants are modifications to the Soyuz-U launcher. The latter is a "light" version without side boosters.

When launched from ELS site, the Soyuz-2 will always be mated with ST-type fairing. This version will be called Soyuz-ST or Soyuz-STK, where additional "K" indicates special measures taken for preparing and launching the rocket in hot and humid conditions.

Soyuz 2.1a

The 2.1a version includes conversion from analog to digital flight control system and uprated engines on the booster and the first stage with improved injection systems. The new digital flight control and telemetry systems allow the rocket to launch from a fixed rather than angled launch platform and adjust its heading in flight. A digital control system also enables the launch of larger commercial satellites with wider and longer payload fairings such as the ST-type fairing. These fairings introduce too much aerodynamic instability for the old analog system to handle. This stage continues to use the RD-0110 engine.

The 2.1a/ST version is sometimes called Soyuz ST-A. The first launch, from Guiana, (17 December 2011 for Pléiades-HR 1A, SSOT, ELISA (4 satellites)) was a success.

Soyuz 2.1b

The 2.1b version adds an upgraded engine (RD-0124) with improved performance to the second stage. First launch took place from Plesetsk Cosmodrome Site 43 on 26 July 2008 with classified military payload.^[7]

The 2.1b/ST version is sometimes called Soyuz ST-B. The first launch, from Guiana, was a success (21 October 2011), for the first two Galileo IOV satellites.

Soyuz 2.1v

The first draft of the 2.1v version was finished in 2009. It is a "light" version of the Soyuz-2 without the side boosters (blocks B, V, G and D). The Block A engine was replaced by the more powerful NK-33-1, which will eventually be replaced with the RD-193. The new launcher is able to deliver up to 2.8 tonnes in low Earth orbit.^[8]

Modifications for various launch sites

The Soyuz-2.1a, 1b and 1v versions launched from the Vostochny Cosmodrome and the Guiana Space Centre have a series of modifications over the stock units. Some of these might later be implemented on all the Soyuz-2, while some are particular requirements to the space port design.

Modifications for the Guiana Space Centre (GSC) version includes:

• First use of a mobile service tower at the ELS that enabled vertical payload integration.^[3]
• European supplied payload adapters.^[3]
• European supplied KSE (French: Kit de Sauvegarde Européenne, lit. European Safeguard Kit), a system to locate and transmit a flight termination signal.^[3] It would activate the engine shutdown command and leave the vehicle in a ballistic trajectory.^[9]
• Adaptation of the S-Band telemetry system on all stages from the 5 TM bands available at Baikonur, and Plesetsk to the 3 allowed at the GSC range.^[3]
• Adaptation of the S-Band telemetry coding and frequency to the IRIG standard used at GSC.^[3]
• Adaptation of the oxygen purge system for directing to the outside of the mobile gantry.^[3]
• Adaptation to the tropical GSC climate including the adaptation of the air conditioning system to local specifications and protective measures to avoid icing.^[3] All holes and cavities were studied and certified to be adequately protected against intrusion of insects and rodent.^[9]
• The four boosters and the core stage were upgraded with pyrotechnic devices to breach the fuel tanks to assure that they would sink in the ocean. The other stages were shown to lose structural integrity on impact and thus proven to sink.^[9]
• At least initially, the boosters and core stage would use the pyrotechnically ignited 14D22 (RD-107A) and 14D23 (RD-108A) rather than the chemically ignited 14D22KhZ and 14D23KhZ used on the rest of the Soyuz-2.^[9]

Modifications for the Vostochny Cosmodrome version includes:^[10]

• New and upgraded computer, N.A.Semikhatov NPO Automatika's Malachite-7, with six times more performance, better obsolescence protection, reduced weight.^[11][12][13]
• The new computer enabled a significant reduction on the cable network complexity thanks to multiplexing lines and using common buses.^[10][13][14]
• New nickel-cadmium batteries that eliminate the need for a dedicated battery charging station.^[11]
• The inclusion of on-board video system, that will enable real-time views of the launch.^[11]
• Since the launch pad at Vostochny also has a mobile gantry for vertical payload integration, similar to the ELS at Guiana, it has the necessary piping to direct the oxygen purges outside of the gantry.^[10]

On 1 October 2015 it was announced that parts of the assembly complex for the Soyuz-2 at Vostochny Cosmodrome were designed for a different modification of the rocket and are too small, so that the planned first launch in December 2015 is under question.^[15]

Suborbital test flight

On 8 November 2004, at 18:30 GMT (21:30 Moscow Time), the first Soyuz-2 carrier rocket, in the Soyuz-2.1a configuration, was launched from the Plesetsk Cosmodrome in Russia. The rocket followed a sub-orbital trajectory, with the third stage and boilerplate payload re-entering over the Pacific Ocean.

Commercial launches

MetOp-A

The first attempt at launching a Soyuz-2 to orbit, with the MetOp-A satellite, occurred on 17 July 2006. It was scrubbed two hours before the launch by an automatic sequence, after the onboard computer failed to check the launch azimuth. Fuelling of the rocket was underway at the time, and all launch complex equipment and on-board preliminary checks had proceeded without incident. The rocket was left fuelled on the launch pad, for the next attempt on 18 July. Launch was eventually conducted on 19 October.

Launch history

See also

Wikimedia Commons has media related to Soyuz (rocket).

• Soyuz programme

References

External links

• Encyclopedia Astronautica article on Soyuz 2.1
• Encyclopedia Astronautica article on Soyuz 2.1/Fregat
• European Space Agency about Soyuz-ST (Russian name Soyuz-STK)
• Soyuz User's Manual, from Starsem
• Soyuz-2 launch vehicle, Russian Federal Space Agency

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