This page no longer updated from 31 October 2001. Latest version can be found at R-6C

Designer: Marquardt. Used on spacecraft: Advent, HS 393. Propellants: N2O4/MMH Thrust(vac): 3 kgf. Thrust(vac): 0.03 kN. Isp: 290 sec. Mass Engine: 1 kg. Diameter: 0.1 m. Length: 0.3 m. Chambers: 1. Chamber Pressure: 6.84 bar. Area Ratio: 100.00. Country: USA. Status: In Production.

A derivative of an Advent Communications satellite thruster in the 1960s, the 6C was qualified in 1981 for the Insat 1, Arbasat 1, and Olympus and HS-393-type satellites.. Manufacturer: Kasier Marquardt. Applications: satellite AOCS. Dry Mass: 0.66 kg. Length: 251.6 mm. Mounting: fixed. Engine Cycle: pressure-fed. Oxidizer: nitrogen tetroxide at 0.005 kg/sec at 15-17 atm. Fuel: MMH at 0.003 kg/sec at 15-17 atm. Mixture Ratio(O/F): 16(0.1. Thrust: 22 N (range 6.2-32.9 N). R-6C-2.2 version operates at 100 N nominal. Isp: 290 sec vacuum at 22 N Thrust: Exit Diameter: 55.9 mm. Expansion Ratio: 100:1. Combustion Chamber: a single chamber of silicide-coated columbium (niobium). Pressure 6.84 atm. Started by electrical signal to on/off solenoid valve. Also has a multiple doublet injector with hypergolic ignition..

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Last update 12 March 2001.
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© Mark Wade, 2001 .