"11.3.6. Nominal thrust of engines at sea level, tf: first stage - 2 x 1200
second stage - 4 x 112.5
11.3.7. Operational lifetime, flights - 1
11.4. Launch vehicle MTKS-I
11.4.1. Dimensions, m:
length - 67.5
height (according to the vertical tail of the OS) - 24
width (according to OS wingspan) - 26
11.4.2. Max characteristics, t:
fully fueled - 2800
at launch - 2786.5
at first stage cut-off - 965.6
at first stage separation - 803.6
at second stage cut-off - 232.2
11.4.3. Nominal thrust of engines at
liftoff, tf - 3626
11.4.4. Thrust-to-weight ratio:
at start - 1.30
second stage (after separation) - 1.24
11.4.5. Payload mass, launched in the OS cargo compartment, t:
to a reference circular orbit of an artificial satellite with a height of 200 km at inclination і =51.6° - 40 (with dV reserve of 120 m/s)
to a polar orbit with Ncr = 200 km - 29.5
to an orbit with a height of Ncr = 400 km at inclination і =97° - 20"