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UR-530
Part of Proton Family
UR-530/Almaz
UR-530/Almaz
In the first half of the 1970's, in competition with Glushko's POS orbital station and RLA series of rockets, Chelomei proposed launch of a 30 tonne version of Almaz into sun synchronous orbit using an upgraded UR-530 launch vehicle. Model of Almaz with VA capsule and escape tower atop the UR-530 at the Memorial Museum of Cosmonautics, September 1994
Credit: © Dietrich Haeseler
1976 design for an upgraded Proton, replacing the first stage with a cluster of six modular stages derived from the UR-100N first stage. Detail design to the draft project stage was undertaken in 1976-1977 but the much larger and more expensive Energia/Buran system was selected for development instead.

Status: Design 1977. Payload: 36,000 kg (79,000 lb). Gross mass: 1,200,000 kg (2,600,000 lb). Height: 56.00 m (183.00 ft). Diameter: 4.15 m (13.61 ft). Span: 7.50 m (24.60 ft). Apogee: 200 km (120 mi).

The UR-530 was designed to place 36 metric tons into low earth orbit or boost large payloads to geostationary orbit, Mars, and Venus. It was also designed for launch of Chelomei's LKS manned spaceplane (30 metric tons into a 97 degree, 200 km sun synchronous orbit). Using existing components, Chelomei showed he could develop a launch system with the same performance as Energia/Buran, but using already-developed storable propulsion technologies. The UR-100N first stages, like the ICBM, would be sealed, certified units, requiring no on-pad processing. The second stage would be a version of the existing Proton second stage.

LEO Payload: 36,000 kg (79,000 lb) to a 200 km orbit at 51.60 degrees. Payload: 30,000 kg (66,000 lb) to a 200 km 97 deg SSO.



Family: orbital launch vehicle. Country: Russia. Agency: Chelomei bureau.

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