Ammonia Jet Propulsion System (APS)
Yuzhnoye Design Bureau
The Ammonia Jet Propulsion System (APS) developed by Yuzhnoye SDO is designed for correction of spacecraft injection errors in orbital period and maintenance of orbital period throughout active spacecraft lifetime. First deployed on the MicroSat-M scientific spacecraft, it uses ammonia as propellant in both hot (catalytic decomposition resistojet) and cold (direct gas expansion) operating modes […]
Key figurescomparable across the catalogue
- Mass
- 24 kg
- Power
- 375 W
- Thrust
- 0.049 N
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
- Propellant
- Ammonia
- Number of Engines
- 2
- Engine Thrust
- 0.049 N
- Total Thrust Impulse (hot mode)
- 7,000 N*s
- Total Thrust Impulse (cold mode)
- 2,500 N*s
- Number of Firings
- Up to 500
- Maximum Firing Duration
- 15 minutes
- Supply Voltage
- 24 to 34 V
- Max Power Consumption (at 28V)
- 375 W
- Dry Mass
- 24 kg
About
The Ammonia Jet Propulsion System (APS) developed by Yuzhnoye SDO is designed for correction of spacecraft injection errors in orbital period and maintenance of orbital period throughout active spacecraft lifetime. First deployed on the MicroSat-M scientific spacecraft, it uses ammonia as propellant in both hot (catalytic decomposition resistojet) and cold (direct gas expansion) operating modes with two engines. The system delivers 0.049 N thrust per engine with a total hot-mode impulse of 7,000 N·s (714 kgf·s) and cold-mode impulse of 2,500 N·s (255 kgf·s). It supports up to 500 firings with maximum firing durations of 15 minutes per firing. The complete system has a dry mass of 24 kg and operates on 24 to 34 V supply voltage. All qualification tests including climatic, mechanical, firing, and endurance testing have been completed.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.