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

Purpose:
Spacecraft (S/C) station keeping.
Year of release: 2016
Guaranteed service life (years):
5000 hours 6000 cycles
Estimated production / delivery time (months): 10
Flight qualification of the product: Yes
Brief history of flight qualification:
As part of OneWeb S/C.
Possibility to adapt the product to customer requirements: Yes


Parameter Value
Discharge power 220/300 W
Discharge voltage 180/300 V
Discharge current 1.2/1.0 A
Thrust 14.8/18.0 mN
Specific impulse 930/1300 s
Efficiency 35%
Specific power 167/227 W/kg
Power-to-thrust ratio 14.9/16.7 W/mN
Total impulse > 0.27/0.4 MN∙s
Mass 1.32 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 40.5 mm.
Low flow rate cathode.
New structural materials and components.

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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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