&sq=Qlik&lang=&file=File:The_second_test_launch_of_Angara-A5_from_the_Plesetsk_cosmodrome.jpg) Launch of Angara A5 | |
| Function | Launch vehicle |
|---|---|
| Manufacturer | Khrunichev KBKhA |
| Country of origin | Russia |
| Cost per launch | Angara A5: US$100 million (2021) [1] |
| Size | |
| Height | 42.7 m (140 ft) - 64 m (210 ft) |
| Width | Angara 1.2 2.9 m (9 ft 6 in) Angara A5 8.86 m (29.1 ft) |
| Mass | 171,500 kg (378,100 lb) - 790,000 kg (1,740,000 lb) |
| Stages | 2-3 |
| Capacity | |
| Payload to LEO (Plesetsk) | |
| Mass | 3,800 kg (8,400 lb) - 24,500 kg (54,000 lb) |
| Payload to GTO (Plesetsk) | |
| Mass | 5,400 kg (11,900 lb) - 7,500 kg (16,500 lb) |
| Associated rockets | |
| Comparable | Naro-1 used a modified URM-1 first stage |
| Launch history | |
| Status | Active |
| Launch sites | Plesetsk, Site 35/1 Vostochny, Site 1A |
| Total launches | 8 (A1.2PP: 1 (suborbital), A1.2: 3, A5: 4) |
| Success(es) | 7 (A1.2PP: 1 (suborbital), A1.2: 3, A5: 3) |
| Partial failure(s) | 1( A5: 1) |
| First flight | A1.2PP: 9 July 2014 A1.2: 29 April 2022 A5: 23 December 2014 |
| Last flight | A1.2: 17 September 2024 A5: 11 April 2024 |
| Boosters (A5) – URM-1 | |
| No. boosters | 4 (see text) |
| Powered by | 1 RD-191 |
| Maximum thrust | 1,920 kN (430,000 lbf) (Sea level) |
| Total thrust | 7,680 kN (1,730,000 lbf) (Sea level) |
| Specific impulse | 310.7 s (3.047 km/s) (Sea level) |
| Burn time | 214 seconds |
| Propellant | RP-1/LOX |
| First stage – URM-1 | |
| Powered by | 1 RD-191 |
| Maximum thrust | 1,920 kN (430,000 lbf) (Sea level) |
| Specific impulse | 310.7 s (3.047 km/s) (Sea level) |
| Burn time | Angara 1.2: 214 seconds Angara A5: 325 seconds |
| Propellant | RP-1/LOX |
| Second stage – URM-2 | |
| Powered by | 1 RD-0124A |
| Maximum thrust | 294.3 kN (66,200 lbf) |
| Specific impulse | 359 s (3.52 km/s) |
| Burn time | Angara A5: 424 seconds |
| Propellant | RP-1/LOX |
| Third stage (A5) – Briz-M (optional) | |
| Powered by | 1 S5.98M |
| Maximum thrust | 19.6 kN (4,400 lbf) |
| Specific impulse | 326 s (3.20 km/s) |
| Burn time | 3,000 seconds |
| Propellant | N2O4/UDMH |
| Third stage (A5) – KVTK (optional, under development) | |
| Powered by | 1 RD-0146D |
| Maximum thrust | 68.6 kN (15,400 lbf) |
| Specific impulse | 463 s (4.54 km/s) |
| Burn time | 1,350 seconds |
| Propellant | LH2/LOX |
The Angara rocket family (Russian: Ангара) is a family of launch vehicles being developed by the Moscow-based Khrunichev State Research and Production Space Center. The launch vehicles are to put between 3,800 kg (8,400 lb) and 24,500 kg (54,000 lb) into low Earth orbit and are intended, along with Soyuz-2 variants, to replace several existing launch vehicles.