VKS-V (original) (raw)

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VKS-V

Part of VKS series

VKS-O

Russian winged orbital launch vehicle. Vertical takeoff, delta winged, single-stage-to-orbit, LOx/Kerosene/LH2 tripropellant rocket engine powered vehicle. 550 metric ton gross liftoff mass and 1000 metric ton versions studied. Analogous to NASA's Shuttle-2 and RKK Energia's VKS.

Status: Study 1988. Payload: 7,500 kg (16,500 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 67,700 kg, with payload 7,500 kg / 1.4 percent of the growth. Payload could therefore be zero 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 1619 m/s compared to 1168 m/s for MAKS (payload 3.1% of gross).

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

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