Stationary Plasma Thruster with a Discharge Power of up to 25 kW
- Purpose: Spacecraft station keeping.Spacecraft orbit raising to GEO.
- Year of release: 2013
- Guaranteed service life (years): 10000 hours
- Estimated production / delivery time (months): 12
- Flight qualification of the product: No
- Brief history of flight qualification: None
- Possibility to adapt the product to customer requirements: Yes
| Parameter | Value |
|---|---|
| Discharge power | ≤ 25000 W |
| Discharge voltage | ≤ 800 V |
| Discharge current | (15-48) A |
| Thrust | ≤ 1070 mN |
| Specific impulse | ≤ 3200 s |
| Efficiency | ≤ 60 % |
| Specific power | ≤ 1000 W/kg |
| Power-to-thrust ratio | ≤ 23 W/mN |
| Total impulse | ≤ 38 MN∙s |
| Mass | 25 kg |
Thruster with a discharge power of up to 25 kW.
Propellant - xenon.
Development status – engineering model.
Consists of the anode and cathode units.
Classical scheme of the magnetic system with magnetic screens and eight external magnetic coils.
Outside diameter of the accelerating channel is 230 mm. Mean diameter of the accelerating channel is 200 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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