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Soyuz 11A511U / Ikar

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Soyuz-U / Globalstar Credit: TsSKB

Status: Design 1999. Payload: 4,100 kg (9,000 lb). Thrust: 4,030.00 kN (905,980 lbf). Gross mass: 305,000 kg (672,000 lb). Height: 43.40 m (142.30 ft). Diameter: 2.95 m (9.67 ft). Apogee: 450 km (270 mi).

The Ikar upper stage was part of the Soyuz launch system upgrade policy. Built by TsSKB in Samara, this fourth stage was derived from an existing flight-proven module that has been used successfully more than 30 times on Yantar spy satellite missions. Equipment and subsystems from the module were used to the maximum extent to limit new development. Modifications were primarily limited to some of command/control equipment and certain mechanical/electrical interfaces with the payload. Ikar had a mass of 820 kg. and was located under the payload fairing. With an in-flight restart capability of up to 50 times, it can handle deployment of multi-satellite payloads to different orbits. The stage can be controlled from the ground or in an operate autonomous mode. The stage was powered by a 17D61 engine from KB Melnikov and had a vacuum thrust of 2.943 kN. It operated on UDMH/N2O4 propellant and had 16 vernier engines for flight control.

LEO Payload: 4,100 kg (9,000 lb) to a 450 km orbit at 51.80 degrees. Payload: 2,750 kg (6,060 lb) to a 800 km SSO. Launch Price $: 50.000 million in 1999 dollars.

Stage Data - Soyuz 11A511U / Ikar

• Stage 0. 4 x 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: In Production. Comments: Gross mass includes 1190 kg of hydrogen peroxide and 280 kg of liquid nitrogen expended during ascent but not contributing to propulsion.

• Stage 1. 1 x 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: In Production. Comments: Gross mass includes 2600 kg of hydrogen peroxide and 520 kg of liquid nitrogen expended during ascent but not contributing to propulsion.

• Stage 2. 1 x 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: In Production.

• Stage 3. 1 x Ikar. Gross Mass: 3,164 kg (6,975 lb). Empty Mass: 820 kg (1,800 lb). Thrust (vac): 2.940 kN (661 lbf). Isp: 326 sec. Burn time: 600 sec. Diameter: 2.72 m (8.92 ft). Span: 2.72 m (8.92 ft). Length: 2.56 m (8.39 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: 17D61. Status: In Production. Comments: Derived from propulsion module of Yantar spysat, over 30 flights to 1998. 50 restarts.