Low Power Stationary Plasma Thruster with 70 mm Diameter of the Accelerating Channel
- Purpose: Spacecraft position keeping.
- Year of release: 1980
- Guaranteed service life (years): 3100 hours 3000 cycles
- Estimated production / delivery time (months): 10
- Flight qualification of the product: Yes
- Brief history of flight qualification: As part of the thrust module (see item 6).
- Possibility to adapt the product to customer requirements: Yes
| Parameter | Value |
|---|---|
| Discharge power | 669 W |
| Discharge voltage | 300 V |
| Discharge current | 2.23 A |
| Thrust | 39 mN |
| Specific impulse | 1470 s |
| Efficiency | 43% |
| Specific power | 446 W/kg |
| Power-to-thrust ratio | 17.2 W/mN |
| Total impulse | > 0.49 MN∙s |
| Mass | 1.5 kg |
Thruster.
Propellant - xenon.
Consists of the anode and cathode units.
Classical scheme of the magnetic system with magnetic screens and four external magnetic coils. Outside diameter of the accelerating channel is 70 mm. Mean diameter of the accelerating channel is 55 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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