Encyclopedia Astronautica
Angara 1.1



angara11.jpg
Angara 1.1
Credit: © Mark Wade
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Angara LV Family
Credit: © Mark Wade
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Briz M
Credit: Khrunichev
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Angara
Credit: © Mark Wade
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Angara Khrunichev
Angara Khrunichev model
Credit: Khrunichev
Russian orbital launch vehicle. The initial flight version would be the Angara 1.1, featuring a single URM core module with the existing Briz upper stage. Payload would be 2.0 tonnes to a 200 km / 63 deg orbit). Other vehicle variants were numbered according to the number of URM's.

LEO Payload: 2,000 kg (4,400 lb) to a 200 km orbit at 63.00 degrees.

Stage Data - Angara 1.1

  • Stage 1. 1 x Angara UM. Gross Mass: 140,000 kg (300,000 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 2,094.700 kN (470,907 lbf). Isp: 338 sec. Burn time: 300 sec. Isp(sl): 310 sec. Diameter: 2.90 m (9.50 ft). Span: 2.90 m (9.50 ft). Length: 25.00 m (82.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-191. Status: Development 2004. Comments: Can be throttled to 95%. Propellant ration 2.6:1, chamber pressure 257 bar.
  • Stage 2. 1 x Angara Briz M. Gross Mass: 6,565 kg (14,473 lb). Empty Mass: 1,600 kg (3,500 lb). Thrust (vac): 19.600 kN (4,406 lbf). Isp: 326 sec. Burn time: 1,000 sec. Diameter: 2.50 m (8.20 ft). Span: 2.50 m (8.20 ft). Length: 2.61 m (8.56 ft). Propellants: N2O4/UDMH. No Engines: 1. Engine: S5.98M. Status: Development 2004. Comments: 8 restarts. Propellant ration 2.0:1.

Status: In development.
Gross mass: 145,000 kg (319,000 lb).
Payload: 2,000 kg (4,400 lb).
Height: 34.90 m (114.50 ft).
Diameter: 3.90 m (12.70 ft).
Thrust: 1,910.00 kN (429,380 lbf).
Apogee: 200 km (120 mi).

More... - Chronology...


Associated Countries
See also
  • Angara The Angara was a new all-Russian heavy launch vehicle designed to replace the Zenit (which was built by a Ukrainian company) and Proton (which had launch pads only on Kazakh territory). The booster was sized for rail transport of modular manufactured components to cosmodromes at Plesetsk and Svobodniy. The design featured a single modular core that could be clustered for large payloads or used as a first stage with a variety of existing upper stages. All plans for the Angara were dependent on financing and subject to constant change. More...

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

Associated Stages
  • Angara Briz M N2O4/UDMH propellant rocket stage. Loaded/empty mass 6,565/1,600 kg. Thrust 19.60 kN. Vacuum specific impulse 325.5 seconds. Version proposed as Angara upper stage. 8 restarts. Propellant ration 2.0:1. More...
  • Angara UM Lox/Kerosene propellant rocket stage. Loaded/empty mass 140,000/10,000 kg. Thrust 2,094.70 kN. Vacuum specific impulse 337.5 seconds. Can be throttled to 95%. Propellant ration 2.6:1, chamber pressure 257 bar. More...

Angara 1.1 Chronology


1994 August 30 - . LV Family: Angara. Launch Vehicle: Angara 1.1.
  • Work starts on Angara launch vehicle - . Nation: Russia. Summary: Ministry of Defence authorizes work to start on Angara launch vehicle. Angara will replace Zenit (built in Ukraine) and Proton as future Russian medium launch vehicle, launched from Plesetsk and Svobodny..

1999 June 12 - . LV Family: Angara. Launch Vehicle: Angara 1.1.
  • Angara cold flow test article exhibited at the Paris Air Show - . Nation: Russia.

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