Modified Thermocatalytic Low Thruster
Glavkosmos
Propellant - hydrazine. The main thruster component parts are: a decomposition chamber with a catalyst element and a nozzle, a propellant injection unit, two small-size solenoid valves that supply propellant to the thruster, and a pressure signaling indicator that monitors the fact that the thruster
Technical specifications
- Thrust
- (0.548 … 0.096)/ (0.113 … 0.096) N
- Propellant inlet pressure
- (880..200)/ (187..168) kPa
- Specific impulse in a continuous mode of operation
- (216..206) s
- Specific impulse in a pulse mode of operation
- (176..200) s
- Life in terms of propellant throughput, kg
- 20(35)/20
- Life in terms of number of cycles
- 80000 (150000) cycles
- Power consumption in the preparation mode and in the instant readiness mode
- (3.3 … 3.9) W
- Power consumption in the forced preparation mode (for 3.5 min, up to 5 times)
- (24.4 … 37.5) W
- Overall dimensions
- 112х70х38 mm
- Mass
- 0.2 kg
About
Propellant – hydrazine. The main thruster component parts are: a decomposition chamber with a catalyst element and a nozzle, a propellant injection unit, two small-size solenoid valves that supply propellant to the thruster, and a pressure signaling indicator that monitors the fact that the thruster has been started up. A resistive heater and MLI installed on the thruster chamber ensure the required thermal mode of the thruster. The thruster also has a mounting plate that joins the thruster elements. Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procured parts and components (6 months).
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.
