Propellant Management Assembly (PMA)
Glavkosmos
The Propellant Management Assembly (PMA) reduces high-pressure propellant and supplies it from a storage unit to an XFC within a required pressure range, specifically for stationary plasma thrusters using xenon.
Key figurescomparable across the catalogue
- Mass
- 3 kg
- Design life
- 10 years
- Lead time
- 12 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
- Design life
- 10 years
- Lead time
- 12 months
- Flight qualification of the product
- Yes
- Possibility to adapt the product to customer requirements
- Yes
- Maximum inlet pressure at a temperature of 40 °c
- 190 kgf/cm2
- Outlet pressure at propellant flow rate
- (1.6 - 1.9 ) kgf/cm2
- Proof pressure / maximum operating pressure
- 1.5:1
- Propellant flow rate at an inlet pressure of 3...190 kgf/cm2
- (2..35) mg/s
- Nominal valve pull-in / drop-out voltage
- 29/10 V
- Heater supply voltage
- (10.0 ± 0.4) V
- Pressure transducer supply current
- 3...12 mA
- Temperature sensor resistance at 0 ⁰s
- (100.00 ± 0.25) Ohm
- Temperature sensor operating current
- ≤ 5 mA
- Mass
- 3 kg
About
The Propellant Management Assembly (PMA) is designed to reduce high-pressure propellant and supply it from a storage unit to an XFC (Xenon Flow Controller) within a specified pressure range. It is specifically intended for propellant supply to stationary plasma thrusters, utilizing xenon as the propellant. The PMA ensures an outlet flow rate of not less than 35 mg/s. Key features include a guaranteed service life of 10 years and the possibility to adapt the product to customer requirements. The product has undergone flight qualification. The estimated production/delivery time is 12 months, not including the time needed to procure materials (4 months) and procured parts and components (6 months).
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.