Low Power Stationary Plasma Thruster with 70 mm Diameter of the Accelerating Channel

    • 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
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    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

    Description

    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
    ... 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.
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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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