Encyclopedia Astronautica
R-6C


Marquardt N2O4/MMH rocket engine. 0.033 kN. In Production. Isp=290s.Derivative of Advent communications satellite thruster for Insat 1, Arbasat 1, and Olympus and HS-393 satellites.

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..

Engine: 0.66 kg (1.45 lb). Chamber Pressure: 6.93 bar. Area Ratio: 100. Thrust to Weight Ratio: 5.08.

Status: In Production.
Unfuelled mass: 0.66 kg (1.45 lb).
Height: 0.25 m (0.83 ft).
Diameter: 0.0559 m (0.1833 ft).
Thrust: 33 N (7 lbf).
Specific impulse: 290 s.

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Associated Propellants
  • N2O4/MMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Monomethylhydrazine (CH3NHNH2) is a storable liquid fuel that found favour in the United States for use in orbital spacecraft engines. Its advantages in comparison to UDMH are higher density and slightly higher performance. More...

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