Oreol Variant 6

Winged orbital launch vehicle. Family:

In the late 1990's the Russian space industry undertook the Orel programme to evaluate technology for future launch vehicles. The goals included evaluation of possible concepts for a future Russian launcher, reusable launch vehicle key technology research and analysis of "X-vehicle" flight demonstrators for technology validation.

Version:

Orel V2. Status: Study 1997.

This preferred near-term configuration was a semi-reusable vertical takeoff/horizontal landing two stage launch vehicle. It would use a flyback booster, expendable second stage, and a small manned spaceplane. This was preferred to the Orel V3, which was essentially the earlier MMKS/OK-M1 system with a flyback booster, expendable core tank, and small spaceplane with recoverable main engines.

LEO Payload: 10,900 kg (24,000 lb). to: 200 km Orbit. at: 51.00 degrees. Liftoff Thrust: 8,090.000 kN (1,818,700 lbf). Total Mass: 550,000 kg (1,210,000 lb). Core Diameter: 22.83 m (74.90 ft). Total Length: 83.00 m (272.00 ft). Version:

Orel V4. Status: Study 1997.

Fully reusable vertical takeoff, horizontal landing two stage to orbit concept. Abandoned in favor of Orel V6.

LEO Payload: 10,000 kg (22,000 lb). to: 200 km Orbit. at: 51.00 degrees. Version:

Orel V5. Status: Study 1997.

Vertically launched two stage to orbit concept consisting of horizontal landing booster, vertical landing orbiter. Abandoned in favor of Orel V6.

LEO Payload: 10,000 kg (22,000 lb). to: 200 km Orbit. at: 51.00 degrees. Version:

Orel V6. Status: Study 1997.

Fully reusable vertical takeoff / horizontal landing single stage to orbit launch vehicle. The preferred long-term alternative of the Russian Orel launch vehicle study of the 1990's.

LEO Payload: 10,000 kg (22,000 lb). to: 200 km Orbit. at: 51.00 degrees. Liftoff Thrust: 12,000.000 kN (2,697,000 lbf). Total Mass: 930,000 kg (2,050,000 lb). Core Diameter: 32.00 m (104.00 ft). Total Length: 58.00 m (190.00 ft). Version:

Orel V7 RSSLV-2. VTOVL orbital launch vehicle. Status: Study 1997.

Fully reusable vertical takeoff / vertical landing single stage to orbit. Concept abandoned in favor of Orel V6 by 1998 due to engine reliability concerns. Version with Lox/LH2 propellants.

LEO Payload: 10,000 kg (22,000 lb). to: 200 km Orbit. at: 51.00 degrees. Total Mass: 1,045,000 kg (2,303,000 lb). Core Diameter: 15.70 m (51.50 ft). Total Length: 42.50 m (139.40 ft). Version:

Orel V7 RSSLV-3. VTOVL orbital launch vehicle. Status: Study 1997.

Fully reusable vertical takeoff / vertical landing single stage to orbit. Concept abandoned in favor of Orel V6 by 1998 due to engine reliability concerns. Tripropellant Lox/Kerosene (RG-1)/LH2 version.