Modified Thermocatalytic Low Thruster
Glavkosmos
A hydrazine monopropellant thermocatalytic thruster used for spacecraft orientation, attitude control, and station keeping, with flight-qualified heritage on multiple Russian satellite programs.
Key figurescomparable across the catalogue
- Mass
- 0.2 kg
- Power
- 3.3 W
- Largest dimension
- 112 mm
- Thrust
- 0.096 N
- Specific impulse
- 206 s
- Data rate
- 20 Mbps
- Design life
- 10.5 years
- Lead time
- 10 months
Normalised to common units so this product can be compared with others in its category. The supplier's own wording is below.
As published by the supplier
- Purpose
- Spacecraft orientation, attitude control, and station keeping
- Year of release
- 2009
- Design life
- 10.5 years
- Lead time
- 10 months
- Flight qualification of the product
- Yes
- Brief history of flight qualification
- As part of: S/C of Cosmos series; Luch series (launched on 11.12.11, 03.11.12, 28.04.14, 28.09.14); Yamal-401 S/C (launched on 14.12.14); S/C of Express series (launched on 26.12.13, 16.03.14, 21.10.14, 14.09.15); S/C of KazSat-3 series (launched on 28.04.14)
- Possibility to adapt the product to customer requirements
- Yes
- 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
- 20(35)/20 kg
- 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
- 112 × 70 × 38 mm
- Mass
- 0.2 kg
- Propellant
- Hydrazine
About
The Modified Thermocatalytic Low Thruster is a hydrazine monopropellant thruster designed for spacecraft orientation, attitude control, and station keeping. It was first released in 2009 and has a guaranteed service life of 10.5 years, with an estimated production/delivery time of 10 months. The product can be adapted to customer requirements. It is flight qualified and has been used on Cosmos series spacecraft, Luch series spacecraft (launched 11.12.11, 03.11.12, 28.04.14, 28.09.14), the Yamal-401 spacecraft (launched 14.12.14), Express series spacecraft (launched 26.12.13, 16.03.14, 21.10.14, 14.09.15), and the KazSat-3 spacecraft (launched 28.04.14). The thruster’s main components include 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 thruster startup. A resistive heater and multi-layer insulation (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 together. Manufacturing lead time does not include time needed to procure materials (4 months) or procured parts and components (6 months).
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.