The ammonium propulsion system (APS) based on electrothermal engines is intended to be used on spacecraft for their orientation and
for orbit correction and change.
- Low thrust level ensuring fine control of spacecraft motion
- Maintenance of serviceability in wide temperature range including negative temperatures
- Increased operational reliability due to simple configuration and design of main assemblies and owing to relatively large diameter of
passage cross sections of the lines
- Low toxicity and fire-and-explosion safety of propulsive mass
- Low cost
- Modular design which allows for installation on various spacecraft without modification.
| Nominal thrust of engine, mN | 50 |
| Specific thrust pulse of engine, m/s | 2700 |
| Total thrust pulse of propulsion system, N s | 2000 |
| Nominal electric power supply voltage, V | 28 |
| Energy value of engine thrust, W/N | 4000 |
| Propulsive mass (ammonia) supply | by pressure of its saturated vapor |
Consumed power, W
- in switched on condition
- in switched off condition |
320
na |
| Service life, years | 15 |
| Probability of failure - free operation | 0.98 |
Due to propulsive mass storage in liquid phase, the ammonium propulsion system has good mass-geometry
characteristics, is simple, reliable, and its exhaust does not contain condensing solid particles. |
Development of company
