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ATS 5 cm
Part of Sert-I engine series Family
EOS electric/cesium rocket engine. Flown in 1968-1969. Thruster for the ATS-4 and ATS-5 tests; consisted of two contact ionization engines using cesium propellant.

Status: Flown in 1968-1969.. Date: 1966-1969. Thrust: 0.0089 N (0.0020 lbf). Specific impulse: 6,700 s.

The thruster anode diameter was 5 cm, and an Yttrium-doped tungsten neutralizer was used. Beam power supply voltage was 3000 V, and the power per thruster was 0.02 kW, producing 0.089 mN thrust at a specific impulse of 6700 seconds. About 0.05 kg of propellant was carried. The longest ground test prior to launch was 2245 hours, and on ATS-4 the thruster operated for about 10 hours (however the test was terminated early because the satellite was put in a useless short-life parking orbit). This was the first successful orbital test of an ion engine, and no electromagnetic interference with satellite subsystems was detected. The second attempted test, on ATS-5, could not be conducted because of a 4G spacecraft spin which could not be damped.

Electrical Input Power: 0.0200 kW.



Country: USA. Propellants: Electric/Cesium. Agency: EOS.

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