Modified Stationary Plasma Thruster with a Discharge Power of up to 5 kW
- Purpose: Spacecraft station keeping.Spacecraft orbit raising to GEO.
- Year of release: 2007
- Guaranteed service life (years): 20000 hours 7000 cycles
- Estimated production / delivery time (months): 12
- Flight qualification of the product: Yes
- Brief history of flight qualification: As part of: SS/Loral’s S/C Airbus Defense & Space S/C.
- Possibility to adapt the product to customer requirements: Yes
| Parameter | Value |
|---|---|
| Discharge power | 3000/4500 W |
| Discharge voltage | 375/300 V |
| Discharge current | 8.0/15.0 A |
| Thrust | 176/290 mN |
| Specific impulse | 1900/1770 s |
| Efficiency | 50/55% |
| Specific power | 370/556 W/kg |
| Power-to-thrust ratio | 17/15.5 W/mN |
| Total impulse | > 14 MN∙s |
| Mass | 8.1 kg |
Thruster with a discharge power of up to 5 kW.
Propellant - xenon.
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 140 mm. Mean diameter of the accelerating channel is 120 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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