Aerospace systems
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Launch vehicle

The Soyuz-FG middle-class launch vehicle (LV) is intended for injection of automatic spacecraft for national economy, scientific research and spacecraft for special purposes as well as manned and cargo spaceships according to the program of the International Space Station.

The three-stage Soyuz-FG LV designed on the base of the Soyuz-U LV.

It can liftoff from launch pads currently operational at the Plesetsk and Baikonur Cosmodromes.

The Soyuz-FG LV is designed as a system with parallel separation of the lateral rocket engine assemblies upon the first stage burnout, and transverse separation of the second stage engine assembly after burnout.

Each LV assembly has its own propulsion unit using non-toxic propellants (oxygen and kerosene).

In contrast to Soyuz-U launch vehicle modernized engines with heightened specific thrust on units of the 1-st and the 2-nd stages, developed for Soyuz-2 LV, are used for Soyuz-FG LV for increasing load-carrying capacity.

Soyuz-FG LV can be equipped with nose fairing of the following diameters: 2.7 m; 3.0 m; 3.3 m; 3.715 m.

Fregat kick stage is designed for payload transfer from open intermediate orbit of a launch vehicle to scheduled orbit of spacecraft injection.

Soyuz-FG LV power potentialities
(with 3.3 m nose fairing)

Cosmodrome Inclination, degree Circular orbit average altitude, km Injected payload mass, kg
Baikonur 51.6 200 7130
64,9 190 6850
70,4 200 6790
Main characteristics
LV type
liquid propellant, three-stage
Control system
autonomous, inertial
Launch liftoff mass, t
Lenght, m
Diameter, m
Confirmed serviceability index