 Soyuz‑2.1v prepared for the launch of the Kosmos 2511 and 2512 military satellites in December 2015 | |
| Function | Small-lift launch vehicle |
|---|---|
| Manufacturer | RKTs 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 toLEO | |
| Altitude | 200 km (120 mi) |
| Orbital inclination | 51.8° |
| Mass | 2,850 kg (6,280 lb) |
| Payload toLEO | |
| 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 | Retired |
| Launch sites | Plesetsk,Site 43/4 |
| Total launches | 13 |
| Success(es) | 12 |
| Partial failure | 1 |
| First flight | 28 December 2013 |
| Last flight | 5 February 2025 |
| 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 – Block I | |
| 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 |
TheSoyuz‑2.1v (Russian:Союз‑2.1в,lit. 'Union‑2.1c',[a]GRAU index:14A15) was a Russian expendablesmall-lift launch vehicle, developed as a derivative of theSoyuz-2 series. It is notable for omitting the four strap-on boosters common to otherR-7 family rockets, making it the first R-7 variant without them.
Developed by theProgress Rocket Space Centre (RKTs Progress) inSamara, the Soyuz‑2.1v was originally known asSoyuz‑1 during early development. Launches were conducted from thePlesetsk Cosmodrome in northwest Russia, and were expected to also be conducted from theVostochny Cosmodrome in eastern Russia,[3] and theBaikonur Cosmodrome inKazakhstan, but none ever took place.[4]
The Soyuz‑2.1v represents a significant departure from previous Soyuz configurations. Unlike its predecessors, it does not utilize four strap-on boosters. Instead, its single core stage is powered by theNK-33 engine, a high-performance engine originally built in the 1970s for the SovietN1 Moon rocket. Due to its fixed configuration, the core stage also employs theRD-0110R vernier engine, which consists of four gimbaled chambers for steering and contributes approximately 230.5kilonewtons (51,800 lbf) of thrust.[5]
A limited number of NK-33 engines were available, leading to plans for replacement by theRD-193, a newer engine derived from theAngara'sRD-191, itself a derivative of theZenit'sRD-170. However, full transition to the RD-193 has not occurred.[6]
The second stage is identical to the third stage of the Soyuz-2.1b, utilizing a singleRD-0124 engine. Most missions also employ theVolga upper stage, adapted from the propulsion system of theYantar reconnaissance satellite. Volga offers a lighter and more cost-effective alternative to theFregat upper stage used on other Soyuz-2 missions.
The Soyuz‑2.1v is optimized for small payloads. From Baikonur, it can deliver up to 2,850 kilograms (6,280 lb) to a 200 km (120 mi) circularlow Earth orbit (LEO) at 51.8° inclination, and up to 2,800 kilograms (6,200 lb) to the same altitude at 62.8° inclination from Plesetsk.[4][7]
| Flight | 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 & 2512 | LEO | Earth observation Radar calibration | Partial failure |
| 3 | 23 June 2017 18:04 | Plesetsk,Site 43/4 | Volga | Kosmos 2519 | LEO | Military satellite, possiblygeodesy projectNivelir [ru] | Success |
| 4 | 29 March 2018 17:38 | Plesetsk,Site 43/4 | — | Kosmos 2525 (EMKA) | SSO | Earth observation | 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. 1) | SSO | Reconnaissance | Success |
| 8 | 1 August 2022 20:25 | Plesetsk,Site 43/4 | Volga | Kosmos 2558 (Nivelir No. 3) | Polar | Surveillance | Success |
| 9 | 21 October 2022 19:20 | Plesetsk,Site 43/4 | Volga | Kosmos 2561 & 2562[8] | 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 |
| 13 | 5 February 2025 03:59 | Plesetsk,Site 43/4 | Volga | Kosmos 2581-2583 (MKA B1-3) | Polar | Final flight of Soyuz 2.1v | Success |
