ДП «Конструкторське бюро «Південне» ім. М.К. Янгеля»"

Liquid-propellant thrusters are incorporated in liquid-propellant jet propulsion systems and generate thrust by propellant exhaust through a supersonic nozzle. 

Cyclone-3 Rocket 100-Newton Thruster

Cyclone-3 Rocket 30-Newton Thruster

Okean-O Spacecraft 30-Newton Thruster

Cyclone-4 Rocket 30-Newton Thruster

Basic Specifications

Parameter

Cyclone-3 thruster

Cyclone-3 thruster

Okean-O thruster

Cyclone-4 thruster

Propellants:

oxidizer

fuel

 

Nitrogen Tetroxide

Unsymmetrical Dimethylhydrazine

Nominal thrust, N

100 30 30 30

Specific impulse in continuous running at nominal propellant inlet pressure, m/s

2600 2000

Chamber pressure, MPa

0,7 0,1

Nominal propellant inlet pressure, MPa

1,35

Oxidizer 0.53

Fuel 0.25

Nominal mixture ratio

1,6 1,3 1,6 1,85

Guaranteed number of ignitions

1300 50000 30000

Total running time, s

200 3600 5600

Duration of a single ignition, s

0,21 / 165 0,21 / 600 0,21 / 2000

Supply voltage, V

28

Mass, kg

1,45 1,3 1,16
UP