Stationary Plasma Thruster with a Nominal Discharge Power of 1350 W
Glavkosmos
A xenon-fueled Stationary Plasma Thruster with a nominal discharge power of 1350 W, designed for spacecraft station keeping and orbit raising, featuring a classical magnetic system and extensive flight heritage.
Key figurescomparable across the catalogue
- Mass
- 3.5 kg
- Power
- 1,350 W
- Thrust
- 0.083 N
- Specific impulse
- 1,600 s
- Total impulse
- 2.6 N·s
- Design life
- 1.03 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
- Year of release
- 1985
- Design life
- 9000 hours 5000 cycles years
- Lead time
- 10 months
- Flight qualification of the product
- Yes
- Brief history of flight qualification
- As part of: S/C of Cosmos series; SS/Loral’s S/C; Airbus Defense & Space S/C; OHB System GmbH S/C; S/C of Express series (launched on 13.10.94, 26.09.96.27.10.99, 12.03.00, 18.04.00.25.06.00.10.06.02, 29.12.03, 24.06.15.28.01.08.11.02.09, 26.12.13.16.03.14.21.10.14.14.09.15); Raduga-1M S/C (launched on 09.12.07, 28.01.10, 12.11.13); S/C of Yamal series (launched on 03.11.12, 15.12.14); Gals S/C launched on 20.01.94, 17.11.95); SESAT (launched on 18.04.00) and others.
- Possibility to adapt the product to customer requirements
- Yes
- Discharge power
- 1350 W
- Discharge voltage
- 300 V
- Discharge current
- 4.5 A
- Thrust
- 83 mN
- Specific impulse
- 1600 s
- Efficiency
- 45%
- Specific power
- 386 W/kg
- Power-to-thrust ratio
- 16.3 W/mN
- Total impulse
- > 2.6 MN∙s
- Mass
- 3.5 kg
- Propellant
- xenon
- Outside diameter of the accelerating channel
- 100 mm
- Mean diameter of the accelerating channel
- 85 mm
- Plume divergence half-angle (90% of ion current)
- 45°
About
This Stationary Plasma Thruster (SPT) is designed for spacecraft station keeping and orbit raising, particularly to Geostationary Earth Orbit (GEO). It operates with xenon propellant and has a nominal discharge power of 1350 W. The thruster consists of anode and cathode units and employs a classical magnetic system with magnetic screens and four external magnetic coils. The outside diameter of the accelerating channel is 100 mm, and the mean diameter is 85 mm. The plume divergence half-angle (90% of ion current) is 45°. The product has a guaranteed service life of 9000 hours and 5000 cycles, with an estimated production/delivery time of 10 months (excluding material and component procurement time). It is flight qualified and has a significant flight heritage, having been used on various spacecraft series including Cosmos, SS/Loral, Airbus Defense & Space, OHB System GmbH, Express, Raduga-1M, Yamal, Gals, and SESAT.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.