Low Power Stationary Plasma Thruster with 50 mm Diameter of the Accelerating Channel

    • Low Power Stationary Plasma Thruster with 50 mm Diameter of the Accelerating Channel

    Purpose:
    Spacecraft (S/C) station keeping.
    Year of release: 1976
    Guaranteed service life (years):
    2500 hours 3000 cycles
    Estimated production / delivery time (months): 10
    Flight qualification of the product: Yes
    Brief history of flight qualification:
    As part of: Meteor-1-27 S/C (launched on 15.05.76); S/C of Kanopus-B series (launched on 22.07.12, 01.02.18, 27.12.18); BKA (launched on 22.07.12); Kanopus-B-IK (launched on 05.07.17); S/C of Cosmos series.
    Possibility to adapt the product to customer requirements: Yes
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    Parameter Value
    Discharge power 220 W
    Discharge voltage 180 V
    Discharge current 1.2 A
    Thrust 14 mN
    Specific impulse 860 s
    Efficiency 26%
    Specific power 179 W/kg
    Power-to-thrust ratio 15.7 W/mN
    Total impulse > 0.13 MN∙s
    Mass 1.23 kg

    Description

    Thruster. Propellant - xenon. Consists of the anode and cathode units. Classical scheme of the magnetic system with magnetic screens and three external magnetic coils. Outside
    ... Thruster.
    Propellant - xenon.
    Consists of the anode and cathode units.
    Classical scheme of the magnetic system with magnetic screens and three external magnetic coils. Outside diameter of the accelerating channel is 50 mm. Mean diameter of the accelerating channel is 40 mm.
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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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