Encyclopedia Astronautica
Sert II

NASA Cleveland electric/mercury rocket engine. 28 mN. Flown in 1970. Isp=4200s. The thruster for the Sert-II test consisted of two electron bombardment engines using mercury propellant.

The thruster anode diameter was 15 cm, and a hollow cathode neutralizer was used. Beam power supply voltage was 3000 V, and the power per thruster was 0.85 kW, producing 28 mN thrust at a specific impulse of 4200 seconds. About 15 kg of propellant was carried. The longest ground test prior to launch was 6742 hours, and in space one engine operated for 2011 hours until a grid short occurred. The second operated for 3781 hours before the neutralizer tank was depleted.

Electrical Input Power: 0.85 kW.

Status: Flown in 1970..
Thrust: 0.0280 N (0.0060 lbf).
Specific impulse: 4,200 s.
First Launch: 1970.

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Associated Propellants
  • Electric/Mercury The many versions of electric engines use electric or magnetic fields to accelerate ionized elements to high velocity, creating thrust. The power source can be a nuclear reactor or thermal-electric generator, or solar panels. Proposed as propellant for some ion motors. More...

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