Encyclopedia Astronautica
Angara 3A



angara3a.jpg
Angara 3A
Credit: © Mark Wade
angara04.jpg
Angara LV Family
Credit: © Mark Wade
Russian orbital launch vehicle. The Angara 3A was a proposed variant of the modular launch vehicle that would use two universal rocket modules (URM's) as boosters flanking one URM in the core, with a Lox/Kerosene upper stage. It could put 14 tonnes into low earth orbit

LEO Payload: 14,000 kg (30,000 lb) to a 200 km orbit at 63.00 degrees.

Stage Data - Angara 3A

  • Stage 1. 2 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 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 3. 1 x Angara A-2. Gross Mass: 25,200 kg (55,500 lb). Empty Mass: 2,355 kg (5,191 lb). Thrust (vac): 294.000 kN (66,093 lbf). Isp: 359 sec. Burn time: 300 sec. Diameter: 2.66 m (8.72 ft). Span: 2.66 m (8.72 ft). Length: 6.70 m (21.90 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-0124. Status: Development 2004. Comments: Two thrust levels. Propellant ration 2.6:1, chamber pressure 162 bar.

Status: In development.
Gross mass: 478,000 kg (1,053,000 lb).
Payload: 14,000 kg (30,000 lb).
Height: 45.00 m (147.00 ft).
Diameter: 3.90 m (12.70 ft).
Thrust: 5,740.00 kN (1,290,400 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 A-2 Lox/Kerosene propellant rocket stage. Loaded/empty mass 25,200/2,355 kg. Thrust 294.00 kN. Vacuum specific impulse 359 seconds. Two thrust levels. Propellant ration 2.6:1, chamber pressure 162 bar. 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...

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