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 N Thruster Cyclone-3 Rocket 30 N Thruster
Okean-O Spacecraft 30 N Thruster Cyclone-4 Rocket 30 N 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 | |
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