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VKS-O
Part of VKS series Family
Russian winged orbital launch vehicle. Vertical takeoff, ballistic re-entry, single-stage-to-orbit, LOx/Kerosene/LH2 tripropellant rocket engine powered, reusable launch vehicle. 550 metric ton and 770 metric ton gross lift-off mass versions considered.

Status: Study 1988. Payload: 8,500 kg (18,700 lb). Gross mass: 550,000 kg (1,210,000 lb). Apogee: 200 km (120 mi).

For the 550 metric ton version, dry mass of the launch vehicle would have to be 68,700 kg / 18 percent of the gross, with payload 8,500 kg / 1.5 percent of the growth. Payload would range from 2000 to 10,000 kg depending on the uncertainties in weight growth of the design during development. As in other vertically-launched SSTO designs, this was considered too great a risk, and the air-launched MAKS was selected instead. Velocity loss during ascent estimated at 1665 m/s compared to 1168 m/s for MAKS (payload 3.1% of gross).

LEO Payload: 8,500 kg (18,700 lb) to a 200 km orbit at 51.00 degrees.



Family: orbital launch vehicle, Winged. Country: Russia. Agency: Molniya bureau.

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