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.
Specifications
- Thrust
- —
- Height
- 46.3 m
- Diameter
- 2.95 m
- Launch mass
- 312 t
- Stages
- 3
- Launch cost
- —
- LEO capacity
- 7,020 kg
- GTO capacity
- 2,810 kg
- GEO capacity
- —
- SSO capacity
- 4,230 kg
Vehicle specifications from Launch Library; blanks are unpublished figures.
Flight record
Counted from padside's own launch record — the same basis as the Stats page.
Launches
- Soyuz STA/Fregat | CSO-2 — Success
- Soyuz STA/Fregat | Falcon Eye 2 — Success
- Soyuz STA/Fregat | CSO-1 — Success
- Soyuz STA/Fregat | SES-15 — Success
- Soyuz STA/Fregat | Sentinel-1B — Success