Vega C
 Model of Vega C at Paris Air Show 2015 | |
| Function | Small-lift launch vehicle |
|---|---|
| Manufacturer | Avio |
| Country of origin | European multi-national[a] |
| Size | |
| Height | 34.8 m (114 ft) |
| Diameter | 3.4 m (11 ft) |
| Mass | 210,000 kg (460,000 lb) |
| Stages | 4 |
| Capacity | |
| Payload toSSO | |
| Altitude | 400 km (250 mi) |
| Mass | 2,450 kg (5,400 lb) |
| Payload topolar orbit | |
| Altitude | 500 km (310 mi) |
| Orbital inclination | 88° |
| Mass | 2,250 kg (4,960 lb) |
| Payload to equatorial elliptical orbit | |
| Altitude | apogee:5,700 km (3,500 mi) perigee:250 km (160 mi) |
| Orbital inclination | 6° |
| Mass | 1,700 kg (3,700 lb) |
| Associated rockets | |
| Family | Vega |
| Comparable | |
| Launch history | |
| Status | Active |
| Launch sites | Guiana Space Centre,ELV |
| Total launches | 2 |
| Success(es) | 1 |
| Failure(s) | 1 (VV22) |
| First flight | 13 July 2022 |
| First stage –P120C | |
| Height | 13.38 m (43.9 ft) |
| Diameter | 3.4 m (11 ft) |
| Gross mass | 155,027 kg (341,776 lb) |
| Propellant mass | 141,634 kg (312,250 lb) |
| Maximum thrust | 4,323 kN (972,000 lbf) |
| Specific impulse | 279 s (2.74 km/s) |
| Burn time | 135.7 seconds |
| Propellant | HTPB/AP/Al |
| Second stage –Zefiro 40 | |
| Height | 8.07 m (26.5 ft) |
| Diameter | 2.4 m (7 ft 10 in) |
| Gross mass | 40,477 kg (89,237 lb) |
| Propellant mass | 36,239 kg (79,893 lb) |
| Maximum thrust | 1,304 kN (293,000 lbf) |
| Specific impulse | 293.5 s (2.878 km/s) |
| Burn time | 92.9 seconds |
| Propellant | HTPB/AP/Al |
| Third stage –Zefiro 9 | |
| Height | 4.12 m (13.5 ft) |
| Diameter | 1.9 m (6 ft 3 in) |
| Gross mass | 12,000 kg (26,000 lb) |
| Propellant mass | 10,567 kg (23,296 lb) |
| Maximum thrust | 317 kN (71,000 lbf) |
| Specific impulse | 295.9 s (2.902 km/s) |
| Burn time | 119.6 seconds |
| Propellant | HTPB/AP/Al |
| Fourth stage – AVUM+ | |
| Height | 2.04 m (6 ft 8 in) |
| Diameter | 2.18 m (7 ft 2 in) |
| Empty mass | 698 kg (1,539 lb) |
| Propellant mass | 492 kg (1,085 lb) ofN2O4,248 kg (547 lb) of UDMH |
| Powered by | 1 ×MEA |
| Maximum thrust | 2.42 kN (540 lbf) |
| Specific impulse | 315.8 s (3.097 km/s) |
| Burn time | Up to 924.8 seconds (up to five burns)[b] |
| Propellant | UDMH/N2O4 |
Vega C,orVega Consolidation,is an expendable small-lift launch vehicle operated byArianespaceand developed and produced byAvio.It is an evolution of the originalVegalauncher, designed to offer greater launch performance and flexibility. Development began after the December 2014 ESA Ministerial Council to address the need to accommodate larger institutional payloads and compete with more affordable launch providers.[1]
Like its predecessor, Vega C is designed to launch smallsatellitesfor scientific andEarth observationmissions topolarandlow Earthorbits.[2]The reference Vega C mission is a polar orbit bringing a spacecraft of 2,300 kilograms (5,100 lb) to an altitude of 700 kilometres (430 mi), an increase of 800 kg (1,800 lb) over the original. The rocket, named afterVega,thebrightest starin the constellationLyra,[3]is a single-body launcher (no strap-on boosters) with threesolidand oneliquidstage. The lead manufacturer to the Vega program is fromItaly,but the rocket has significant contributions from companies based inBelgium,France,Netherlands,Spain,SwitzerlandandUkraine.
The Vega C incorporates several key improvements over the original Vega. The first-stage motor is replaced by the more potent P120C, a shared propulsion system with the Ariane 6 launcher. The second stage is the more powerful Zefiro 40, while the AVUM+ upper stage has more propellant than the original. The Zefiro 9 third stage remains unchanged.[4]
Vega rockets are launched from theELVlaunch pad at theGuiana Space Centre.Vega C's maiden flight on 13 July 2022 successfully deliveredLARES 2and six other satellites to orbit.[5]However, the second launch on 21 December 2022 experienced a failure of the Zefiro 40 second stage, resulting in the loss of twoPléiades NeoEarth-imaging satellites.[6]Consequently, the next launch was delayed until late 2024 to allow for the rocket motor nozzle to be redesigned.[7]
Specifications[edit]
Stages[edit]
| Stages[8] | Stage 1 P120C |
Stage 2 Zefiro 40 |
Stage 3 Zefiro 9 |
Stage 4 AVUM+ |
|---|---|---|---|---|
| Height | 13.38 m (43 ft 11 in) | 8.07 m (26 ft 6 in) | 4.12 m (13 ft 6 in) | 2.04 m (6 ft 8 in) |
| Diameter | 3.4 m (11 ft 2 in) | 2.4 m (7 ft 10 in) | 1.9 m (6 ft 3 in) | 2.18 m (7 ft 2 in) |
| Propellant type | Solid | Solid | Solid | Liquid |
| Gross mass | 155,027 kg (341,776 lb) | 40,477 kg (89,237 lb) | 12,000 kg (26,000 lb) | 1,436 kg (3,166 lb) |
| Propellant mass | 141,634 kg (312,250 lb) | 36,239 kg (79,893 lb) | 10,567 kg (23,296 lb) | 740 kg (1,630 lb) |
| Average thrust | 4,323 kN (972,000 lbf) | 1,304 kN (293,000 lbf) | 317 kN (71,000 lbf) | 2.45 kN (550 lbf) |
| Burn time (sec.) | 135.7 | 92.9 | 119.6 | 924.8 (up to 5 burns)[b] |
| Specific impulse | 279 s (2.74 km/s) | 293.5 s (2.878 km/s) | 295.9 s (2.902 km/s) | 315.8 s (3.097 km/s) |
Main suppliers[edit]
Building the Vega is a European multi-national effort led byAvioofItaly,which manages Vega development and oversees production as the prime contractor, and also builds the Zefiro 40, Zefiro 9 and AVUM+ stages. Europropulsion, a 50-50 joint venture of Avio andArianeGroup,builds the P120C first stage. Dutch Space of theNetherlandsbuilds the interstage between the first and second stages. CIRA builds the interstage between the second and third stages.RUAGofSwitzerlandbuilds the payload fairing.SABCAofBelgiumbuilds the thrust vector control systems.[8]
Payload[edit]
Arianespacehad indicated that the Vega launcher is able to carry 2,300 kg (5,100 lb) to a circularpolar orbitat an altitude of 700 km (430 mi).[9]
Because of its ability to carry heavier payloads,RUAG Spaceof Switzerland had to redesign thefairingof the Vega C.
The fairing is 3.3 m (11 ft) in diameter and over 9 m (30 ft) tall, which offers nearly double the payload volume of the original Vega, which had a fairing of 2.6 m (8 ft 6 in) in diameter and over 7.8 m (26 ft) tall.[10]
Ascent timeline[edit]
This is a timeline of a typical Vega C ascent profile and associated sequence of events that includes two AVUM+ boosts. However, the flight profile is optimized for each mission.
| Event[8] | Time (sec.) |
Altitude km (mi) |
Velocity m/s (ft/s) |
|---|---|---|---|
| P120C ignition & lift-off | 0 | 0 | 0 |
| P120C burn-out & separation, Zefiro 40 ignition | 142 | 60 (37) | 1,885 (6,180) |
| Zefiro 40 burn-out & separation | 245 | 121 (75) | 4,555 (14,940) |
| Zefiro 9 ignition | 249 | 123 (76) | 4,550 (14,900) |
| Fairing jettisoning | 254 | 126 (78) | 4,600 (15,000) |
| Zefiro 9 separation | 417 | 190 (120) | 7,564 (24,820) |
| AVUM+ 1st ignition | 448 | 199 (124) | 7,553 (24,780) |
| AVUM+ 1st cut-off | 1,090 | 300 (190) | 7,885 (25,870) |
| AVUM+ 2nd ignition | 3,151 | 619 (385) | 7,533 (24,710) |
| AVUM+ 2nd cut-off | 3,287 | 623 (387) | 7,631 (25,040) |
| Spacecraft separation | 3,427 | 626 (389) | 7,627 (25,020) |
Future[edit]
Building on Vega C, Vega E (or Vega Evolution) is a further evolution of the Vega C with the Zefiro 9 and AVUM+ third and fourth stage replaced with a cryogenic upper stage powered byliquid oxygenandliquid methane.This variant offers even more flexibility than Vega C, with the ability to deliver multiple satellites into different orbits on a single launch.
As of March 2021[update]Avio is finalizing the development of the newM10methane engine used in the new upper stage. The engine design is the result of a collaboration between Avio andChemical Automatics Design Bureau(KBKhA) ended in 2014.[11][4]
Avio successfully conducted the first series of testing of theM10engine between May and July 2022[12]with the maiden flight of the Vega-E planned for 2027.[13]
See also[edit]
- List of Vega launches
- Solid rocket
- Comparison of orbital launchers families
- Comparison of orbital launch systems
Notes[edit]
- ^The lead manufacturer is fromItaly,but the rocket has significant contributions from companies based inBelgium,France,Netherlands,Spain,SwitzerlandandUkraine.
- ^abEngines can burn up to 612.5 seconds per burn and can burn up to five times. Maximum cumulative burn time of 924.8 seconds.
References[edit]
- ^"Media backgrounder for ESA Council at Ministerial Level".esa.int.ESA. 27 November 2014.Retrieved2021-01-17.
- ^Amos, Jonathan (13 February 2012)."Vega launcher makes first flight".BBC News.Retrieved13 February2012.
- ^Tariq Malik (13 February 2012)."Europe Launches New Vega Rocket on Maiden Voyage".Space.Retrieved29 May2014.
The Italian-built Vega rocket is named after the second-brightest star in the northern hemisphere
- ^ab"VEGA C".Avio.Retrieved2021-01-17.
- ^European Space Agency, ed. (2022-07-13)."Vega-C successfully completes inaugural flight".esa.int.Retrieved2022-07-14.
- ^"Europe's Vega C rocket fails on 2nd-ever mission, 2 satellites lost".Space.21 December 2022.
- ^Foust, Jeff (October 2, 2023)."ESA delays Vega C return to flight to late 2024".Spacenews.
- ^abc"Vega C Users Manual"(PDF).Arianespace.May 2018. p. 1-6.Retrieved2024-07-08.
- ^"Vega C Overview".Arianespace.
- ^"Vega-C".esa.int.Retrieved2024-07-04.
- ^Bellomi, P.; Rudnykh, M.; Carapellese, S.; Liuzzi, D.; Caggiano, G.; Arione, L.; Gurtovoy, A.A.; Lobov, S.D.; Rachuk, V. S.; D'Aversa, E.; De Lillis, A.; Pellegrini, R. C. (2019-02-08)."Development of LM10-MIRA liquid oxygen – liquid natural gas expander cycle demonstrator engine".Progress in Propulsion Physics – Volume 11.pp. 447–466.Bibcode:2019EUCAS..11..447B.doi:10.1051/eucass/201911447.ISBN978-5-94588-228-7.S2CID139531422.Retrieved2021-03-23.
- ^"First Half 2022 Financial Report".Avio(Press release). 9 September 2022.Retrieved16 September2022.
- ^"First Half 2023 Financial Report"(PDF).Avio.Retrieved10 September2023.
