Vega C
European small-lift launch vehicle From Wikipedia, the free encyclopedia
Vega C, or Vega Consolidation,[1] is a European expendable, small-lift launch vehicle developed and produced by Avio. It is an evolution of the original Vega launcher, designed to offer greater launch performance and flexibility.
 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 to SSO | |
| Altitude | 700 km (430 mi) |
| Orbital inclination | 90° |
| Mass | 2,300 kg (5,100 lb) |
| Payload to polar 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 | 3 |
| Success(es) | 2 |
| Failure(s) | 1 (VV22) |
| First flight | 13 July 2022 |
| Last flight | 5 December 2024 |
| 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) of N2O4, 248 kg (547 lb) of UDMH |
| Powered by | 1 × RD-843 (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 |
Approved for development by the European Space Agency (ESA) in December 2014, Vega C was designed to accommodate larger institutional payloads and compete effectively in the commercial launch market.[2] Initially marketed and operated by Arianespace, the ESA decided in August 2024 to empower Avio to directly commercialize Vega C and seek non-governmental customers. This transition is anticipated to be complete by the end of 2025.[3][4]
Vega C, like its predecessor, is designed to launch small satellites for scientific and Earth observation missions to polar and sun-synchronous low Earth orbits.[5] The reference Vega C mission places a 2,300-kilogram (5,100 lb) spacecraft into a 700-kilometre (430 mi) polar orbit, representing an 800-kilogram (1,800 lb) or 60% increase over the original Vega.
Named after Vega, the brightest star in the constellation Lyra,[6] the rocket is a single-body launcher (no strap-on boosters) with three solid and one liquid stage. While Avio of Italy leads the Vega program, contributions come from companies in Belgium, France, the Netherlands, Spain, Switzerland and Ukraine.
Vega C introduces several key advancements over the original Vega. The first stage has been replaced by the more powerful P120C, the "C" refers to its common design allowing it to be used as a booster for the Ariane 6 launcher, enabling shared development costs. The second stage features the upgraded Zefiro 40. While the AVUM+ (Attitude & Vernier Upper Module) fourth stage remains largely unchanged, the "+" reflects its increased propellant capacity. The third stage, Zefiro 9, remains the same.[7]
Vega rockets are launched from the ELV launch pad at the Guiana Space Centre. The Vega C's maiden flight on 13 July 2022 successfully delivered LARES 2 and six other satellites to orbit.[8] However, the second launch on 21 December 2022 experienced a failure of the Zefiro 40 second stage, resulting in the loss of two Pléiades Neo Earth-imaging satellites.[9] Consequently, the next launch was delayed until late 2024 to allow for the rocket motor nozzle to be redesigned.[10]
Specifications
Summarize
Perspective
Stages
| Stages[11] | 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 (HTPB/AP/Al) |
Solid (HTPB/AP/Al) |
Solid (HTPB/AP/Al) |
Liquid (UDMH/N2O4) |
| 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
Building the Vega is a European multi-national effort led by Avio of Italy, 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 and ArianeGroup, builds the P120C first stage. Dutch Space of the Netherlands builds the interstage between the first and second stages. The Italian Aerospace Research Centre builds the interstage between the second and third stages. Beyond Gravity of Switzerland builds the payload fairing and onboard GNC computer.[12] SABCA of Belgium builds the thrust vector control systems.[11]
Payload capacity
Arianespace had indicated that the Vega C launcher is able to carry 2,300 kg (5,100 lb) to a circular polar orbit at an altitude of 700 km (430 mi).[13]
Because of its ability to carry heavier payloads, Beyond Gravity had to redesign the fairing of the Vega C. The new 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.[14]
Ascent timeline
This timeline of a typical Vega C ascent profile and associated sequence of events includes two AVUM+ boosts. However, the flight profile is optimized for each mission.
| Event[11] | 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
Vega-C+
A mid-life upgrade for the Vega-C, the Vega-C+ replaces the P120C first stage with the P160C first stage, enabling higher payload and performance.[15]
Vega-E
Building on Vega C, the Vega E (or Vega Evolution) is a further development of the Vega family with a larger P160C first stage and the Zefiro 9 and AVUM+ third and fourth stages replaced with a single upper stage powered by liquid oxygen and liquid methane. The improvements are expected to improve payload capacity by 25% over Vega C.[16] This design would enable multiple satellites to be launched into different orbits on a single launch. The engine for this new upper stage, the M10, was the result of a collaboration between Avio and Chemical Automatics Design Bureau (KBKhA).[17][7] Successful testing of the engine was conducted in 2022,[18] and the maiden flight of Vega E is anticipated in 2027.[19] Launch Complex 3 at the Guiana Space Centre, which initially built for the Ariane 5, will be refurbished to support Vega E launches.[16]
Avio also plans to develop a new methane-fueled first-stage engine with plans to introduce a partially reusable rocket to eventually replace the Vega.[20]
List of launches
Launch history
| Flight | Date / time (UTC) | Rocket | Launch site | Payload | Payload mass | Orbit | Customers | Launch outcome |
|---|---|---|---|---|---|---|---|---|
| VV21 | 13 July 2022 13:13:17[21] |
Vega C | ELV |
|
350 kg (770 lb) | MEO | Success | |
| First flight of Vega C | ||||||||
| VV22 | 21 December 2022 01:47:31[22] |
Vega C | ELV | Pléiades Neo 5 & 6 | 1,977 kg (4,359 lb) | SSO | Airbus Defence and Space | Failure |
| Earth observation satellites.[23] Failure due to loss of pressure of the Zefiro 40 second stage.[24] | ||||||||
| VV25 | 5 December 2024 21:20:33[25] |
Vega C | ELV | Sentinel-1C | 2,300 kg (5,100 lb) | SSO | ESA | Success |
| Third Sentinel-1 satellite. Return to flight for Vega C following the VV22 launch failure.[24] | ||||||||
Future launches
| Date / time (UTC) [26] | Rocket | Launch site | Payload | Orbit |
|---|---|---|---|---|
| March 2025[27] | Vega C VV26 |
ELV | BIOMASS | SSO |
| Earth observation satellite. Part of the Living Planet Programme. | ||||
| June 2025[28][29] | Vega C VV27 |
ELV | CO3D × 4 MicroCarb |
SSO |
| Earth observation satellites | ||||
| September 2025[30] | Vega C VV28 |
ELV | SMILE | HEO |
| Joint Chinese-European Earth observation satellite. | ||||
| November 2025[31] | Vega C VV29 |
ELV | PLATiNO-2 / MAIA | SSO |
| PLATiNO-2 will host the MAIA instrument payload. | ||||
| Q4 2025[32] | Vega C VV30 |
ELV | IRIDE × ? | LEO |
| First launch for the Italian IRIDE Earth observation satellite constellation. | ||||
| Q3 2025[33] | Vega C | ELV | KOMPSAT-6 (Arirang-6) | SSO |
| Earth observation satellite. | ||||
| Q3 2025[34] | Vega C | ELV | SSMS #9 | LEO |
| SSMS #9 rideshare mission. Delayed due to the VV22 Vega-C launch failure.[35] | ||||
| Q3 2025[34] | Vega C | ELV | SSMS #7 | SSO |
| SSMS #7 rideshare mission. | ||||
| Q3 2025[36] | Vega C[37] | ELV | Sentinel-3C | SSO |
| Third Sentinel-3 Earth observation satellite.[38] | ||||
| Q3 2025[34] | Vega C | ELV | SSMS #13 | SSO |
| SSMS #13 rideshare mission. | ||||
| Q4 2025[32] | Vega C | ELV | IRIDE × ? | LEO |
| Second launch for the Italian IRIDE Earth observation satellite constellation. | ||||
| 2025[34] | Vega C | ELV | SSMS #8 | SSO |
| SSMS #8 rideshare mission. | ||||
| TBD[39] | Vega C | ELV | PLATiNO-1 | SSO |
| Earth observation satellite. | ||||
| 2025[34] | Vega C | ELV | SSMS #6 | SSO |
| SSMS #6 rideshare mission. | ||||
| 2025[34] | Vega C | ELV | SSMS #10 | SSO |
| SSMS #10 rideshare mission. | ||||
| 2025[40] | Vega C | ELV | CSG-3 | SSO |
| Third COSMO-SkyMed 2nd Generation satellite. | ||||
| 2025[41][42] | Vega C[43] | ELV | SHALOM | SSO |
| Joint Italian-Israeli hyperspectral imaging satellite. | ||||
| January 2026[44] | Vega C | ELV | KOMPSAT-7 (Arirang-7) | SSO |
| Earth observation satellite[45][46] | ||||
| Q2 2026[34] | Vega C | ELV | SSMS #14 | SSO |
| SSMS #14 rideshare mission. | ||||
| Q3 2026[34] | Vega C | ELV | SSMS #15 | LEO |
| SSMS #15 rideshare mission to an equatorial orbit. | ||||
| Q3 2026[34] | Vega C | ELV | SSMS #16 | LEO |
| SSMS #16 rideshare mission to an equatorial orbit. | ||||
| Q4 2026[36] | Vega C[37] | ELV | CO2M-A (Sentinel-7A) | SSO |
| Copernicus Anthropogenic Carbon Dioxide Monitoring. Part of the Copernicus Programme. | ||||
| 2026[47] | Vega C | ELV | ALTIUS, FLEX | SSO |
| ALTIUS is an ozone observation satellite. FLEX is an Earth observation satellite of the Living Planet Programme. | ||||
| 2026[48] | Vega C | ELV | ClearSpace-1 | LEO |
| Space debris removal demo. | ||||
| 2026[49] | Vega C | ELV | CSG-4 | SSO |
| Fourth COSMO-SkyMed 2nd Generation satellite. | ||||
| 2026[50] | Vega C | ELV | EAGLE-1 | LEO |
| Demonstrator satellite for the first European sovereign space-based quantum key distribution system.[51] | ||||
| Q1 2027[36] | Vega C[37] | ELV | CO2M-B (Sentinel-7B) | SSO |
| Copernicus Anthropogenic Carbon Dioxide Monitoring. Part of the Copernicus Programme. | ||||
| Q2 2027[34] | Vega C | ELV | SSMS #17 | LEO |
| SSMS #17 rideshare mission. | ||||
| 2027[15] | Vega C+ | ELV | Space Rider | LEO |
| Technology demonstration[52] | ||||
| 2027[53][54] | Vega C[55] | ELV | FORUM | SSO |
| Earth observation satellite. Part of the Living Planet Programme. | ||||
| Q2 2028[34] | Vega C | ELV | SSMS #18 | LEO |
| SSMS #18 rideshare mission. | ||||
| Q4 2028[36] | Vega C[56] | ELV | CRISTAL (Sentinel-9) | Polar |
| Copernicus Polar Ice and Snow Topography Altimeter. Part of the Copernicus Programme. | ||||
| Q4 2028[34] | Vega C | ELV | SSMS #19 | LEO |
| SSMS #19 rideshare mission. | ||||
| 2028[36] | Vega C[57] | ELV | Sentinel-3D | SSO |
| Fourth Sentinel-3 Earth observation satellite.[38] | ||||
| Q2 2029[34] | Vega C | ELV | SSMS #20 | LEO |
| SSMS #20 rideshare mission. | ||||
| Q3 2029[36] | Vega C[58] | ELV | CIMR-A (Sentinel-11A) | SSO |
| Copernicus Imaging Microwave Radiometer. Part of the Copernicus Programme. | ||||
| Q4 2029[34] | Vega C | ELV | SSMS #21 | LEO |
| SSMS #21 rideshare mission. | ||||
| 2029[58] | Vega C | ELV | CHIME (Sentinel-10) | SSO |
| Copernicus Hyperspectral Imaging Mission. Part of the Copernicus Programme. | ||||
| 2029[58] | Vega C | ELV | LSTM (Sentinel-8) | SSO |
| Copernicus Land Surface Temperature Monitoring. Part of the Copernicus Programme. | ||||
| 2030[59] | Vega C | ELV | TRUTHS | LEO |
| Traceable Radiometry Underpinning Terrestrial- and Helio-Studies. | ||||
See also
Notes
- The lead manufacturer is from Italy, but the rocket has significant contributions from companies based in Belgium, France, Netherlands, Spain, Switzerland and Ukraine.
References
External links
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