Soyuz-2-1v

(Redirected from Soyuz 2.1v)

The Soyuz 2.1v (Russian: Союз 2.1в, Union 2.1v), GRAU index 14A15,[3] known early in development as the Soyuz 1, is a expendable Russian medium-lift launch vehicle. It is derivative of the Soyuz 2 but utilizing a single core stage (no boosters) built around the powerful NK-33 engine, 50-year-old refurbished remnants from the Soviet N1 moon rocket. It is a member of the R-7 family of rockets built by Progress in Samara. Launches have been conducted from the Plesetsk Cosmodrome in northwest Russia, and are expected to be conducted in the future from the Vostochny Cosmodrome in eastern Russia,[4] and the Baikonur Cosmodrome in Kazakhstan.[5]

Soyuz 2.1v
Launch of an Soyuz 2.1v carrying Kosmos 2525 military satellite on 28 March 2018.
FunctionMedium-lift launch vehicle
ManufacturerProgress
Country of originRussia
Size
Height44 m (144 ft)
Diameter3 m (9.8 ft)
Mass158,000 kg (348,000 lb)
Stages2
Capacity
Payload to LEO
Altitude200 km (120 mi)
Orbital inclination51.8°
Mass2,850 kg (6,280 lb)
Payload to LEO
Altitude200 km (120 mi)
Orbital inclination62.8°
Mass2,800 kg (6,200 lb)
Associated rockets
FamilyR-7 (Soyuz)
Based onSoyuz 2
ComparableLong March 2C
PSLV
Launch history
StatusActive
Launch sitesPlesetsk, Site 43
Total launches12
Success(es)11
Partial failure(s)1
First flight28 December 2013
Last flight9 February 2024
First stage
Height27.77 m (91.1 ft)
Diameter2.95 m (9 ft 8 in)
Empty mass11,000 kg (24,000 lb)
Gross mass129,000 kg (284,000 lb)
Powered by
Maximum thrust
  • NK-33A SL: 1,515 kN (341,000 lbf)
  • NK-33A vac: 1,687 kN (379,000 lbf)
  • RD-0110R SL: 230.5 kN (51,800 lbf)
  • RD-0110R vac: 265 kN (60,000 lbf)
Specific impulse
  • NK-33A SL: 297 s (2.91 km/s)
  • NK-33A vac: 331 s (3.25 km/s)
  • RD-0110R SL: 259.4 s (2.544 km/s)
  • RD-0110R vac: 298.4 s (2.926 km/s)
Burn time225 seconds
PropellantLOX / RP-1
Second stage
Height7.95 m (26.1 ft)
Diameter3 m (9.8 ft)
Empty mass2,380 kg (5,250 lb)
Gross mass25,380 kg (55,950 lb)
Powered by1 × RD-0124
Maximum thrust294 kN (66,000 lbf)
Specific impulse359 s (3.52 km/s)
Burn time275 seconds
PropellantLOX / RP-1
Third stage (optional) – Volga[1]
Height1.025 m (3 ft 4.4 in)
Diameter3.2 m (10 ft)
Empty mass840 kg (1,850 lb)
Propellant mass300–900 kg (660–1,980 lb)
Powered by1 × 17D64[2]
Maximum thrust2.94 kN (660 lbf)
Specific impulse307 s (3.01 km/s)
Burn time410 seconds
PropellantN2O4 / UDMH

Vehicle

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Base of first stage, with NK-33 & RD-0110R engines

The Soyuz 2.1v represents a major departure from earlier Soyuz rockets. Unlike the Soyuz 2 upon which it is based, it does away with the four boosters used on all other R-7 vehicles. The single first stage core stage is built around the powerful single-chamber NK-33 engine replacing the four-chamber RD-108 along with structural modifications. Since the NK-33 is fixed, the stage is also equipped with complex engine RD-0110R, built of four vernier engines (with four chambers and four nozzles) for thrust vector control. The RD-0110R engines add 230.5 kN (51,800 lbf) thrust and heats the pressurization gases.[6]

The NK-33 engines were built in the 1970s for the cancelled Soviet N1 Moon rocket. These surplus engines offer increased performance over the RD-108; however, only a limited number of engines are available. Once the supply is exhausted, the NK-33 will be replaced by the RD-193. In April 2013, it was announced that the RD-193 engine had completed testing. The RD-193 is a lighter and shorter engine based on the Angara's RD-191, which is itself a derivative of the Zenit's RD-170.[7]

The second stage of the Soyuz 2.1v is the same as the third stage of the Soyuz 2.1b;[8] powered by an RD-0124 engine. Most missions will use a Volga upper stage to transfer the payload from an initial parking orbit to its final destination. The Volga is derived from the propulsion system of the Yantar reconnaissance satellite, and was developed as a lighter and cheaper alternative to the Fregat that is used on many Soyuz 2 missions.

The Soyuz 2.1v was designed to serve lighter payloads with a payload capacity of 2,850 kg (6,280 lb) to a 200 km (120 mi) circular low Earth orbit with an inclination of 51.8° from Baikonur, and 2,800 kg (6,200 lb) to a 200 kilometre orbit at 62.8° from Plesetsk.[5][9]

List of launches

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Flight No. Date (UTC) Launch site Upper stage Payload Orbit Remarks Outcome
1 28 December 2013
13:30
Plesetsk, Site 43/4 Volga Aist 1, SKRL-756 #1/2 LEO Maiden flight of Soyuz 2.1v Success
2 5 December 2015
15:08
Plesetsk, Site 43/4 Volga Kosmos 2511 and 2512 LEO Earth observation Radar calibration Partial failure
3 23 June 2017
18:04
Plesetsk, Site 43/4 Volga Kosmos 2519 LEO Military satellite, possibly geodesy project Nivelir [ru]-ZU Success
4 29 March 2018
17:38
Plesetsk, Site 43/4 Kosmos 2525 (EO MKA) SSO Military Satellite Success
5 10 July 2019
17:14
Plesetsk, Site 43/4 Volga Kosmos 2535 to 2538 LEO Geodesy Success
6 25 November 2019
17:52
Plesetsk, Site 43/4 Volga Kosmos 2542 & 2543 LEO Satellite inspection Success
7 9 September 2021
19:59
Plesetsk, Site 43/4 Volga Kosmos 2551 (EO MKA No.2) SSO Reconnaissance Success
8 1 August 2022
20:25
Plesetsk, Site 43/4 Volga Kosmos 2558 (Nivelir No.3) PO Surveillance Success
9 21 October 2022
19:20
Plesetsk, Site 43/4 Volga Kosmos 2561 & 2562[10] SSO Surveillance Success
10 29 March 2023
19:57
Plesetsk, Site 43/4 Kosmos 2568 (EO MKA No.4) SSO Reconnaissance Success
11 27 December 2023
07:03
Plesetsk, Site 43/4 Kosmos 2574 (Razbeg No.1) SSO Reconnaissance Success
12 9 February 2024
07:03
Plesetsk, Site 43/4 Kosmos 2575 (Razbeg No. 2) SSO Reconnaissance Success

See also

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References

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  1. ^ "Volga upper stage". russianspaceweb.com. Retrieved 10 March 2016.
  2. ^ "Soyuz 2-1 launches maiden mission from Vostochny". nasaspaceflight.com. 27 April 2016. Retrieved 1 May 2016.
  3. ^ "Rus/Souyz-2 launch vehicle" (in Russian). Plesetsk Cosmodrome. Retrieved 30 December 2013.
  4. ^ Peslyak, Alexander (24 July 2013). "Vostochny Cosmodrome clears the way to deep space". rbth.co.uk. Russia Beyond The Headlines. Retrieved 30 December 2013.
  5. ^ a b ""Soyuz-1" middle class launch vehicle". Samara Space Centre. Archived from the original on 19 April 2009. Retrieved 11 April 2009.
  6. ^ "Steering engine RD0110R (14D24) Carrier rocket "Soyuz-2.1v"" (in Russian). KBKhA. Retrieved 1 June 2015.
  7. ^ "New engine for light rocket "Soyuz" prepare for mass production at the end of the year" (in Russian). Новости космонавтики. Retrieved 8 April 2013.
  8. ^ Zak, Anatoly. "Origin of the Soyuz-1 project". RussianSpaceWeb. Retrieved 30 December 2013.
  9. ^ "Soyuz -2.1 B". 10 November 2014.
  10. ^ "Ракета «Союз-2.1в» с секретными военными спутниками стартовала с космодрома Плесецк". 21 October 2022.