Stationary Plasma Thruster with a Nominal Discharge Power of 1350 W

Purpose:
Spacecraft station keeping.Spacecraft orbit raising to GEO
Year of release: 1985
Guaranteed service life (years):
9000 hours 5000 cycles
Estimated production / delivery time (months): 10
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


Parameter Value
Discharge power 1350 W
Discharge voltage 300 V
Discharge current 4.5 A
Thrust 83 мН
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

Description

Thruster with a nominal discharge power of 1350 W. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and four external magnetic coils.
... Thruster with a nominal discharge power of 1350 W.
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 100 mm. Mean diameter of the accelerating channel is 85 mm.
Plume divergence half-angle (90% of ion current) is 45°

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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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