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Vulcan Centaur

Vulcan Centaur

Space Launch Systems
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Basic Information
Name
Vulcan Centaur
Designation
Vulcan Centaur
Alternate Designation
Equipment Type
Space Launch Systems
Manufacturer
United Launch Alliance
Date of Introduction
2025
Description

The United Launch Alliance (ULA) Vulcan Centaur is a heavy space launch vehicle leveraging technologies from the Delta IV and Atlas V rockets along with new technologies and innovative features. The new launch vehicle can place a payload of up to 35 tons into Low Earth Orbit (LEO), a 16 ton payload into Geosynchronous Transfer Orbit (GTO) and 7 tons payload into Geosynchronous Earth Orbit (GEO). The Vulcan Centaur vehicle features a first stage, called Vulcan, with a core booster and up to six GEM 63XL strap-on solid rocket boosters. All in, the first stage produces up to 3.8 million pounds of thrust at liftoff compared with 2.6 million pounds of thrust produced by the Atlas V rocket. The second stage is a Centaur vehicle with RL10 engines which drives the ACES upper stage with the five meters long payload fairing containing the spacecraft. In October 2018, the US Air Force (USAF) awarded ULA a $967 million contract for the Vulcan Centaur development under the Evolved Expandable Launch Vehicle (EELV) program. The Vulcan Centaur space launch vehicle is expected perform its first launch in 2020 and to enter service in the early 2020s (2023-2024). The new generation space launch vehicle is expected to outstand by its reliability and cost effectiveness/affordability with the ability to operate in the CisLunar space (the area of space between the Moon and the Earth) to lower fuel consumption thanks to diminished gravity. ULA projects to produce up to 20 rockets per year. The Vulcan Centaur family of space launch vehicles will feature variants with two GEM 63XL rocket boosters, six GEM 63XL rocket boosters and an additional variant called Vulcan Centaur Heavy.

Overview (Deagel)
Group Space Launch Systems
Status Active
Origin United States of America
Contractor United Launch Alliance
Initial Operational Capability (IOC) August 13, 2025
First Flight January 8, 2024
Total Production 2
Development Cost USD $967 million
Unitary Cost USD $200 million
Specifications (Deagel)
Number of Stages 2
Dimensions — Height 61.6 meter
Dimensions — Rocket Diameter 5.4 meter
Mass — Max Lift-off Thrust 1,724 ton
Mass — Max Lift-off Weight 547 ton
Mass — Payload to GEO 7,200 kilogram
Mass — Payload to GTO 16,300 kilogram
Mass — Payload to LEO 34,900 kilogram
Mass — Payload to Moon 12,100 kilogram
Gear (Deagel)
Item 1 Rocket Engines: BE-4 (2)
Item 2 Rocket Engines: GEM 63XL (6)
Item 3 Rocket Engines: RL10C (1)
Details
Country of Origin United States
Classification
Domain
Air & Air Defense
Equipment Status
Active
Dimensions
Length
Width
5.4 m
Height
61.6 m
Weight
547000 kg
Operators (1)
United States
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