Encyclopedia Astronautica
Soyuz 11A511U / Ikar



soylvgl5.jpg
Soyuz-U / Globalstar
Credit: TsSKB
Russian orbital launch vehicle. Standard Soyuz universal booster with the Ikar upper stage, derived from the propulsion system for the Kozlov Yantar series of spy satellites.

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.

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

More... - Chronology...


Associated Countries
Associated Engines
  • 17D61 Melnikov N2O4/UDMH rocket engine. 2.943 kN. Ikar stage 4 for Soyuz-Ikar. Design 1999. Isp=325s. Derived from propulsion module of Yantar spysat, with over 30 flights to 1998. Increased versatility compared to Block L due to capability for 50 restarts. More...

See also
  • R-7 The world's first ICBM became the most often used and most reliable launch vehicle in history. The original core+four strap-on booster missile had a small third stage added to produce the Vostok launch vehicle, with a payload of 5 metric tons. Addition of a larger third stage produced the Voskhod/Soyuz vehicle, with a payload over 6 metric tons. Using this with a fourth stage, the resulting Molniya booster placed communications satellites and early lunar and planetary probes in higher energy trajectories. By the year 2000 over 1,628 had been launched with an unmatched success rate of 97.5% for production models. Improved models providing commercial launch services for international customers entered service in the new millenium, and a new launch pad at Kourou was to be inaugurated in 2011. It appeared that the R-7 could easily still be in service 70 years after its first launch. More...

Associated Manufacturers and Agencies
  • Korolev Russian manufacturer of rockets, spacecraft, and rocket engines. Korolev Design Bureau, Kaliningrad, Russia. More...

Associated Stages
  • Ikar N2O4/UDMH propellant rocket stage. Loaded/empty mass 3,164/820 kg. Thrust 2.94 kN. Vacuum specific impulse 326 seconds. Derived from propulsion module of Yantar spysat, over 30 flights to 1998. 50 restarts. More...
  • Soyuz 11A511U-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,200/2,355 kg. Thrust 298.10 kN. Vacuum specific impulse 330 seconds. More...
  • Soyuz 11A511U-0 Lox/Kerosene propellant rocket stage. Loaded/empty mass 44,500/3,784 kg. Thrust 994.30 kN. Vacuum specific impulse 310 seconds. Gross mass includes 1190 kg of hydrogen peroxide and 280 kg of liquid nitrogen expended during ascent but not contributing to propulsion. More...
  • Soyuz 11A511U-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 105,400/6,875 kg. Thrust 997.09 kN. Vacuum specific impulse 311 seconds. Current version. Gross mass includes 2600 kg of hydrogen peroxide and 520 kg of liquid nitrogen expended during ascent but not contributing to propulsion. More...

Home - Browse - Contact
© / Conditions for Use