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Angara 5A

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Angara 5A Credit: © Mark Wade

Status: Active. First Launch: 2014-12-23. Last Launch: 2014-12-23. Number: 1 . Payload: 28,500 kg (62,800 lb). Thrust: 9,560.00 kN (2,149,170 lbf). Gross mass: 790,000 kg (1,740,000 lb). Height: 64.00 m (209.00 ft). Diameter: 3.90 m (12.70 ft). Apogee: 200 km (120 mi).

LEO Payload: 28,500 kg (62,800 lb) to a 200 km orbit at 63.00 degrees.

Stage Data - Angara 5A

• Stage 1. 4 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 KVRB. Gross Mass: 23,300 kg (51,300 lb). Empty Mass: 3,500 kg (7,700 lb). Thrust (vac): 73.500 kN (16,523 lbf). Isp: 461 sec. Diameter: 4.10 m (13.40 ft). Span: 4.10 m (13.40 ft). Length: 8.60 m (28.20 ft). Propellants: Lox/LH2. No Engines: 1. Engine: RD-56M. Status: Development 2004. Comments: 5 restarts.

Photo Gallery

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Angara LV Family Credit: © Mark Wade

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• IPM - . Nation: Russia. Class: Technology. Type: Re-entry test vehicle. USAF Sat Cat: 40355 . COSPAR: 2014-085A. Apogee: 39,083 km (24,285 mi). Perigee: 36,163 km (22,470 mi). Inclination: 0.91 deg. Period: 1,530.92 min.

  First launch of the Angara-A5 booster, composed of five standard URM-1 modules and a Briz-M upper stage. Four URM-1's, clustered around a URM-1 in the core, formed the first stage. The core URM-1 was the second stage. The four first stage URM-1's separated at 06:01 GMT at an altitude of 82 km; the core URM-1 shut down and separated at 06:03 GMT at an altitude of 148 km, reentering downrange near Tomsk. The nose fairing was jettisoned 10 seconds later. The third stage was a URM-2, powered by the RD-0124A engine; it reached a marginally suborbital trajectory and, after separating from the upper composite section, reentered in the Philippine Sea at a range of 2320 km from the launch site. Meanwhile, the fourth stage, a standard Briz-M (S/N 88801) propelled the stack into a 250 km, 63 deg parking orbit with a burn starting at 06:11 GMT. After coasting to the equator, two perigee burns at 07:03 and 09:26 GMT boosted the apogee to 5,000 km and then 35,800 km, while reducing inclination to 60.6 deg. The Briz-M's additional propellant tank (DTB), now empty, was jettisoned into a 433 km x 35,808 km x 60.6 deg orbit. The payload on this flight was a dummy satellite called the IPM. The stack coasted to apogee and at 14:44 GMT, began the fourth burn to enter circular geosynchronous orbit. At 14:57 GMT the Briz sent a simulated separation command, but the payload remained attached to the stage as intended. After a few more hours, two burns of the Briz stage's SOZ auxiliary engines moved the stack to a graveyard orbit a few hundred kilometers above GEO. This was the first GEO mission ever launched from Plesetsk.