Soyuz-U & -FG rockets
The Soyuz-U and -FG rockets are of the R-7 rocket family, originally developed from the R-7 ballistic missile, which first flew in 1957. The Soyuz rockets launch both the Progress cargo ships and manned Soyuz-TM spaceships (the latter replaced by the TMA version from 2002). The Soyuz-FG is a new version, with a modifed fuel injection system (форсуночная Головка – Forsunochnaya Golovka, fuel-injector’s head) on the engines of the first and second stages, but both have the same 11S510-PVB Blok-I third stage.
Technical data
| Model | R-7 family |
| Code | 11A511U (FG: 11A511FG) |
| Class | Middle |
| Type | One-start |
| Developer | TsKB-Progress State Research & Production Rocket & Space Center |
| Fuel (all stages) | Kerosene |
| Oxidizer (all stages) | LOX (Liquid Oxygen) |
| Number of stages | 3 |
| Stage 1 length & diameter (mm) | 19 600; 3820 |
| Stage 2 length & diameter (mm) | 27 138; 2950 (FG: 31 800 length) |
| Stage 3 length & diameter (mm) | 7145; 2660 (FG: 6745 length) |
| Stage 1 engines | 4 × RD-117 (FG: RD-107A) Four-chamber liquid-propellant rocket engine with two verniers chambers |
| Thrust | 102 000 kg each |
| Stage 2 engines | 1 × RD-118 (FG: RD-108A) Four-chamber liquid-propellant rocket engine with two verniers chambers |
| Thrust | 96 000 kg |
| Stage 3 engines | 1 × RD-0110 Four-chamber LPRE with 4 verniers chambers |
| Thrust | 30 000 kg |
| Total height (mm): | 51 100 (FG: 49 476) |
| Diameter (mm) | 10 300 |
| Start mass | 313 000 kg (FG: 305 000 kg) |
| Payload lift capacity | 8000 kg |
From the NASA Expedition Crew Press Kits:
| First Stage Data - Blocks B, V, G, D (Б, В, Г, Д) | |
|---|---|
| Engine | RD-107 (Soyuz-U rocket has RD-118; Soyuz-FG has RD-107A) |
| Propellants | LOX/Kerosene |
| Thrust (tons) | 102 |
| Burn time (sec) | 122 |
| Specific impulse | 314 |
| Length (meters) | 19.8 |
| Diameter (meters) | 2.68 |
| Dry mass (tons) | 3.45 |
| Propellant mass (tons) | 39.63 |
| Second Stage Data, Block A (А) | |
| Engine | RD-108 |
| Propellants | LOX/Kerosene |
| Thrust (tons) | 96 |
| Burn time (sec) | 314 |
| Specific impulse | 315 |
| Length (meters) | 28.75 |
| Diameter (meters) | 2.95 |
| Dry mass (tons) | 6.51 |
| Propellant mass (tons) | 95.7 |
| Third Stage Data, Block I (И) | |
| Engine (meters) | RD-0110 |
| Propellants | LOX/Kerosene |
| Thrust (tons) | 30 |
| Burn time (sec) | 240 |
| Specific impulse | 330 |
| Length (meters) | 8.1 |
| Diameter (meters) | 2.66 |
| Dry mass (tons) | 2.4 |
| Propellant mass (tons) | 21.3 |
| Payload mass (tons) | 6.8 |
| Shroud mass (tons) | 4.5 |
| Launch mass (tons) | 309.53 |
| Total length | 49.3 |
| Time (min: s) | Event | Altitude |
|---|---|---|
| T −0 | Lift-off | – |
| T +1:58 | First-stage separation | 45 km |
| T +2:40 | Escape tower & launch fairing jettison | 85 km |
| T +4:58 | Second-stage separation | 170 km |
| T +9:00 | Third-stage cut-off | 205 km |
Soyuz-2
«Союз-2»
The Soyuz-2 is a modernized version of the rocket that is intended to replace the Soyuz-U, Soyuz-FG and Molniya-M rockets with one universal version. A digital control system installed in the equipment bay of the third stage increases the rocket’s accuracy, stability and controllability, allowing it to be fitted with a larger-sized shroud (ST fairing – external diameter of 4.110 m, length of 11.400 m) for its payloads . The use of advanced engines on the first and second stages, and a new engine on the third stage (the RD-0124) allows the rocket to increase its payload capability by 1000-1200 kg. The RD-0124 adds an extra 34 seconds of specific impulse that improves the rocket’s performance.
| RD-0110 | RD-0124 | |
|---|---|---|
| Thrust in vacuum: | 298.03 kN | 294.3 kN |
| Specific Impulse: | 326 seconds | 359 seconds |
| Combustion chamber pressure: | 6.8 MPa | 15.53 MPa |
| Engine mass: | 408 kilograms | 450 kilograms |
The Soyuz-2 was tested in two launch stages. The first launch, Soyuz-2-1A, had new control systems and telemetry devices, and the first and second stages used the modernized engines. It successfully took place on 8 November 2004 at the Plesetsk Cosmodrome for a suborbital misson with a test payload. The second Soyuz-2-1A launch took place on 19 October 2006 when MetOp-A, Europe’s first polar-orbiting satellite dedicated to operational meteorology, was put into orbit.
The launch of the Soyuz-2-1B rocket was in 21 December 2006, carrying a satellite called COROT. Helium tanks are fitted inside the oxygen tank for the 1B.
The Soyuz-2 is part of a European-Russian co-operative program.
In the near-future, from 2011, it is planned to launch the next modernized version of the Soyuz manned spaceship on the Soyuz-2 rocket from Kourou, Europe’s Spaceport in French Guiana, as well as unmanned payloads from 2008. The latter will be a Soyuz-2 variant called the Soyuz-ST that includes the Fregat upper stage and ST fairing.
The Fregat is a fourth stage that can reach orbit and operate autonomously as an orbital vehicle.
More details:
- Russian Space Web: Soyuz-2 launch vehicle (14A14)
- Starsem: Modernized Soyuz
- TsKB-Progress: Ракета-носитель «Союз-2»
Rus-M
A new launcher, the Rus-M, was to be produced by the Samara Space Center, who came up with the preliminary design in 2010. It was intended to carry the future PKNP spaceship, itself a Soyuz spaceship replacement. The launcher would replace the Soyuz-FG rocket, and was to be constructed by 2015.
The two-stage Rus-M was to have three variants:
- Variant 1 –16 tons to low orbit. The first stage has 3 inseparable boosters.
- Variant 2 –35 tons to low orbit. Uses 5 boosters on the first stage, four of which are strap-ons that separate first.
- Variant 3 –50 tons to low orbit. The first stage is stretched to allow for more propellant.
The first stage would use the RD-180 engine; the second the RD-0146 engine. The latter engine would use liquid hydrogen and oxygen.
On 7 October 2011, however, Roskosmos chief Vladimir Popovkin announced that the rocket had been cancelled as 37% of funds for Roskosmos had been allocated to developing the Rus-M, but funding overall was small, so it was decided to continue using the Soyuz rockets and possibly the Angara rocket family. The latter is still in development by Khrunichev, with a first launch set for 2013.
Diagrams
- Energiya: Rus-M launcher (157 KB), from the SpaceOps 2010 Presentations documents page
- ESA: Diagram of the Soyuz rocket with a Soyuz spaceship and Progress spaceship inside (122 KB)
- TsENKI: Diagram of the Soyuz-U with a Soyuz spaceship in the payload fairing (38 KB)
Links
- ESA Permanent Mission in Russia: Soyuz launch vehicle
- Russian Space Web: R7 family, Launch vehicle for PPTS spacecraft
- Samara Space Center (ФГУП ГНПРКЦ «ЦСКБ-Прогресс»): manufacturers of the Soyuz rocket and other launch vehicles
- Starsem, the Soyuz company: website for the company that undertakes commercial launches of Soyuz rockets and payloads. There is a Soyuz user’s manual that can be downloaded from the Soyuz performance page.
~ Page last updated: 19/10/2010
Photo gallery
Liftoff of the Soyuz TM-31 rocket, 31 October 2000.
RD-107 first-stage engine – the Soyuz-U rocket has a modified version, the RD-118; Soyuz-FG has RD-107A
RD-108 second-stage engine – the Soyuz-U rocket has a modified version, the RD-117; Soyuz-FG has RD-108A
RD-0110 third-stage engine