Low Power Stationary Plasma Thruster with 50 mm Diameter of the Accelerating Channel
- Purpose: Spacecraft (S/C) station keeping.
- Year of release: 1976
- Guaranteed service life (years): 2500 hours 3000 cycles
- Estimated production / delivery time (months): 10
- Flight qualification of the product: Yes
- Brief history of flight qualification: As part of: Meteor-1-27 S/C (launched on 15.05.76); S/C of Kanopus-B series (launched on 22.07.12, 01.02.18, 27.12.18); BKA (launched on 22.07.12); Kanopus-B-IK (launched on 05.07.17); S/C of Cosmos series.
- Possibility to adapt the product to customer requirements: Yes
| Parameter | Value |
|---|---|
| Discharge power | 220 W |
| Discharge voltage | 180 V |
| Discharge current | 1.2 A |
| Thrust | 14 mN |
| Specific impulse | 860 s |
| Efficiency | 26% |
| Specific power | 179 W/kg |
| Power-to-thrust ratio | 15.7 W/mN |
| Total impulse | > 0.13 MN∙s |
| Mass | 1.23 kg |
Thruster.
Propellant - xenon.
Consists of the anode and cathode units.
Classical scheme of the magnetic system with magnetic screens and three external magnetic coils. Outside diameter of the accelerating channel is 50 mm. Mean diameter of the accelerating channel is 40 mm.
Remark
Manufacturing lead time is given without taking into account the time needed to procure materials (4 months) and procured parts and components (6 months).
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