Angara 3A

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 metric tons 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.