|
R-6C
|
|
Designer: Marquardt. Propellants: N2O4/MMH. Thrust(vac): 33 N (7 lbf). Isp: 290 sec. Mass Engine: 0.66 kg (1.45 lb). Diameter: 0.0559 m (0.1833 ft). Length: 0.25 m (0.83 ft). Chambers: 1. Chamber Pressure: 6.93 bar. Area Ratio: 100.00. Thrust to Weight Ratio: 5.08. 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..
|
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2007 except where otherwise noted.
|
|
|
|