The electric jet propulsion system (EJPS) based on Hall engines is intended to be used on space objects for inter-orbital transfer,
orbit correction and stabilization. 
Main Advantages
- Low thrust level ensuring precision control of a space object
- High specific thrust pulse
- Maintenance of serviceability in wide temperature range including negative temperatures
- Non toxicity and fire-and-explosion safety of propulsive mass
- High reliability due to duplication of main units and assemblies
- Modular design allowing for installation on different space objects.
Technical Characteristics
| Type of Engine | Stationary Plasma Engine or with Anode Layer |
| Propulsive mass | Xenon | | Nominal thrust of engine, mN | 40 |
| Specific thrust pulse of engine, m/s | 16000 |
| Energy value of engine thrust, W/N | 16500 |
| Total thrust pulse of propulsion system, Ns | 1.2*106 |
| Maximal consumed power of propulsion system, W | äî 800 |
| Service life, years | 15 | | Resource of engine, h | 300 |
| Probability of failure - free operation | 0.98 |
The experience of operation of similar type of engines showed their high effectiveness and reliability.
Availability of plasma in engine exhaust practically does not effect the solar arrays service life and radio signals exchange between
a space object and ground tracking stations. |
Development of company
