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MVKS

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AKA: VKS. Status: Design 1986. Payload: 25,000 kg (55,000 lb). Gross mass: 700,000 kg (1,540,000 lb). Unfuelled mass: 200,000 kg (440,000 lb). Height: 71.00 m (232.00 ft). Diameter: 10.00 m (32.00 ft). Span: 42.00 m (137.00 ft). Apogee: 200 km (120 mi).

At NPO Energia Tsybin was appointed the Chief Designer for the project. The Energia VKS was designed as a hypersonic rocketplane with multi-regime engines. These engines were turbo-ramjet with in-line rocket chambers. The VKS was sketched out as having a 700 metric ton takeoff mass, of which 140 metric tons was structure. A 25 metric ton payload could be delivered to a 200 km / 51 degree orbit. Length would have been 71 m, wingspan 42 m, and height 10 m to the top of the fuselage.

Work was abandoned as the Soviet Union broke up. In any case the Tupolev Tu-2000 seemed the preferred solution and had been funded for development of a subscale prototype.

• Government decree orders design of a Soviet aerospaceplane - . Nation: Russia. Spacecraft: Tu-2000, VKS, Yakovlev MVKS. In reaction to US X-30 project government decree ordered development of a Soviet equivalent..

• Government decree orders development of a Soviet aerospaceplane - . Nation: Russia. Spacecraft: Tu-2000, VKS, Yakovlev MVKS. The decree of 27 January 1986 was reaffirmed..

• MVKS specification issued - . Nation: Russia. Spacecraft: Tu-2000, VKS, Yakovlev MVKS.

  The Ministry of Defence issued technical specifications on 1 September for an MVKS, a single-stage reusable aerospaceplane system. The MKVS was to provide effective and economic delivery to near-earth orbit; develop the technology for effective transatmospheric flight; provide super high-speed intercontinental transport, and fulfil military objectives in and from space.