AKA: RTV-G-10;RV-A-10;SSM-A-13;SSM-G-13. Thrust: 2,670.00 kN (600,230 lbf). Gross mass: 110,000 kg (240,000 lb). Apogee: 24 km (14 mi).
Hermes C1 was the subject of a feasibility study for a long-range ballistic missile authorized in June 1946. The original recommended Hermes C1 was a two-stage, 113 metric ton missile powered by 450-kN rocket engines, with a range of over 3200 km. Six engines in clusters of two would make up the first stage, providing a total of 2700 kN of thrust at lift-off and burning for 60 seconds. The second stage would have one motor, and burn for 60 seconds. The 450 kg warhead would separate after burnout of the second stage and glide at hypersonic speed to its target. However GE was ordered to give the other Hermes projects more priority, and didn't turn in the feasibility study for the C1 to the Army until October 1950. The Chief of Ordnance found it valuable, and ordered that it be further refined, while stopping short of authorizing active development of the concept by GE. Instead von Braun's team, just moved to the Redstone Arsenal in Huntsville, Alabama, were asked to pursue in-house development of a single-engine, single-stage version, the Hermes C, as a tactical ballistic missile. This would begin flying three years later as the Redstone missile. Interestingly, the clustered-engine concept would emerge again in April 1957 as the Saturn I.
Maximum range: 60 km (37 mi). Boost Propulsion: Liquid Propellant.