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Russian expendable carrier rocket From Wikipedia, the free encyclopedia
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]
 Launch of an Soyuz 2.1v carrying Kosmos 2525 military satellite on 28 March 2018. | |
| Function | Medium-lift launch vehicle |
|---|---|
| Manufacturer | Progress |
| Country of origin | Russia |
| Size | |
| Height | 44 m (144 ft) |
| Diameter | 3 m (9.8 ft) |
| Mass | 158,000 kg (348,000 lb) |
| Stages | 2 |
| Capacity | |
| Payload to LEO | |
| Altitude | 200 km (120 mi) |
| Orbital inclination | 51.8° |
| Mass | 2,850 kg (6,280 lb) |
| Payload to LEO | |
| Altitude | 200 km (120 mi) |
| Orbital inclination | 62.8° |
| Mass | 2,800 kg (6,200 lb) |
| Associated rockets | |
| Family | R-7 (Soyuz) |
| Based on | Soyuz 2 |
| Comparable | Long March 2C PSLV |
| Launch history | |
| Status | Active |
| Launch sites | Plesetsk, Site 43 |
| Total launches | 12 |
| Success(es) | 11 |
| Partial failure(s) | 1 |
| First flight | 28 December 2013 |
| Last flight | 9 February 2024 |
| First stage | |
| Height | 27.77 m (91.1 ft) |
| Diameter | 2.95 m (9 ft 8 in) |
| Empty mass | 11,000 kg (24,000 lb) |
| Gross mass | 129,000 kg (284,000 lb) |
| Powered by | |
| Maximum thrust |
|
| Specific impulse |
|
| Burn time | 225 seconds |
| Propellant | LOX / RP-1 |
| Second stage | |
| Height | 7.95 m (26.1 ft) |
| Diameter | 3 m (9.8 ft) |
| Empty mass | 2,380 kg (5,250 lb) |
| Gross mass | 25,380 kg (55,950 lb) |
| Powered by | 1 × RD-0124 |
| Maximum thrust | 294 kN (66,000 lbf) |
| Specific impulse | 359 s (3.52 km/s) |
| Burn time | 275 seconds |
| Propellant | LOX / RP-1 |
| Third stage (optional) – Volga[1] | |
| Height | 1.025 m (3 ft 4.4 in) |
| Diameter | 3.2 m (10 ft) |
| Empty mass | 840 kg (1,850 lb) |
| Propellant mass | 300–900 kg (660–1,980 lb) |
| Powered by | 1 × 17D64[2] |
| Maximum thrust | 2.94 kN (660 lbf) |
| Specific impulse | 307 s (3.01 km/s) |
| Burn time | 410 seconds |
| Propellant | N2O4 / UDMH |
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]
| 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-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 |
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