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Orbital launch vehicle. Year: 2000. Other Family: R-7. Country: Russia. Status: Design 2000. Standard Soyuz universal booster with the Fregat upper stage, derived from the propulsion system for Lavochkin interplanetary probes. The Fregat upper stage has a flight-proved propulsion subsystem that is based on a single-chamber Lavochkin engine. Four clusters of three 50-N hydrazine thrusters provide attitude control. The Fregat propulsion system powered the Fobos probe to Mars, and the main engine was fitted on nearly 30 interplanetary spacecraft. During its numerous missions, the engine demonstrated the highest reliability under extreme conditions, exceeding technical specifications. This application of proven, in-production hardware ensures high reliability and lower cost for the Fregat upper stage. Fregat operates on UDMH fuel and N2O4 oxidizer, and has a liftoff mass of up to 6,535 kg. The weight at burnout is 950-1,100 kg.. Vacuum thrust is 19.6 kN., and burn time is up to 877 sec. The engine can be restarted as many as 20 times. Manufacturer: Korolev. LEO Payload: 5,000 kg (11,000 lb). to: 450 km Orbit. at: 51.80 degrees. Payload: 2,700 kg (5,900 lb). to a: sun synchronous, 800 km, 98.6 deg inclination trajectory. Apogee: 500 km (310 mi). Liftoff Thrust: 4,030.000 kN (905,980 lbf). Total Mass: 305,000 kg (672,000 lb). Core Diameter: 2.95 m (9.67 ft). Total Length: 46.10 m (151.20 ft). Launch Price $: 50.000 million. in: 1999 price dollars.
Stage Data - Soyuz 11A511U / Fregat - Stage Number: 0. 4 x Stage: Soyuz 11A511U-0. Gross Mass: 44,500 kg (98,100 lb). Empty Mass: 3,784 kg (8,342 lb). Thrust (vac): 994.300 kN (223,528 lbf). Isp: 310 sec. Burn time: 120 sec. Isp(sl): 264 sec. Diameter: 2.68 m (8.79 ft). Span: 2.68 m (8.79 ft). Length: 19.60 m (64.30 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-107-11D511. Status: Design 2000. Gross mass includes 1190 kg of hydrogen peroxide and 280 kg of liquid nitrogen expended during ascent but not contributing to propulsion.
- Stage Number: 1. 1 x Stage: Soyuz 11A511U-1. Gross Mass: 105,400 kg (232,300 lb). Empty Mass: 6,875 kg (15,156 lb). Thrust (vac): 997.091 kN (224,155 lbf). Isp: 311 sec. Burn time: 286 sec. Isp(sl): 245 sec. Diameter: 2.95 m (9.67 ft). Span: 2.95 m (9.67 ft). Length: 27.80 m (91.20 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-108-11D512. Status: Design 2000. Gross mass includes 2600 kg of hydrogen peroxide and 520 kg of liquid nitrogen expended during ascent but not contributing to propulsion.
- Stage Number: 2. 1 x Stage: Soyuz 11A511U-2. Gross Mass: 25,200 kg (55,500 lb). Empty Mass: 2,355 kg (5,191 lb). Thrust (vac): 298.100 kN (67,016 lbf). Isp: 330 sec. Burn time: 250 sec. Diameter: 2.66 m (8.72 ft). Span: 2.66 m (8.72 ft). Length: 6.74 m (22.11 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-0110. Status: Design 2000.
- Stage Number: 3. 1 x Stage: Fregat. Gross Mass: 6,535 kg (14,407 lb). Empty Mass: 1,100 kg (2,400 lb). Thrust (vac): 19.600 kN (4,406 lbf). Isp: 327 sec. Burn time: 877 sec. Diameter: 3.35 m (10.99 ft). Span: 3.35 m (10.99 ft). Length: 1.50 m (4.90 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: S5.92. Status: In production. Upper stage developed from propulsion bus for Lavochkin lunar and planetary probes (Luna Ye-8, Mars M1, Fobos 1F). 20 restarts.
Bibliography and Further Reading - Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...
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