Angara 5A
Launch vehicle · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: © Mark Wade
Russian orbital launch vehicle. The Angara 5A was a proposed variant of the modular launch vehicle that would use four universal rocket modules (URM's) as boosters surrounding one URM in the core, with a LOx/LH2 upper stage. It could put 5.0 metric tons into geosynchronous orbit, or 8.0 metric tons into geosynchronous transfer orbit.
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.
Related
- Family
- orbital launch vehicle
- Country
- Russia
- Launch Sites
- Plesetsk
- Stages
- Angara UM, Angara KVRB
- Agency
- Chelomei bureau
Photo Gallery
Angara LV Family
Credit: © Mark Wade
Chronology
1 event
2014 December 23
05:57 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk. LV Family: Angara. Launch Vehicle: Angara 5A.- 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.