Adjustment and Braking Engine
- Purpose: Unmanned Spacecraft reactive control system
- Year of release: 2010
- Flight qualification of the product: Letter "O", flight use
- Possibility to adapt the product to customer requirements: Yes
| Parameter | Value |
|---|---|
| Propellants, Fuel/Oxidizer | UDMH/NTO |
| Total Nominal Thrust | 464.0 N |
| One Thruster Nominal Thrust | 116.0 N |
| Nominal Specific Impulse of Thruster, Steady State | 2,855 m/s |
| Nominal Inlet Pressure | 1.47 MPa |
| Inlet Operating Pressure | 1.37…1.57 MPa |
| Total Firing Time, up to | 2,000 s |
| Cycle Life, Number of Starts-up, up to | 5,000 |
| Nozzle Expansion Ratio | 53 |
| Operating Voltage | 27 V |
| Mass, not over | 8.0 kg |
Propulsive burn formation for center of mass velocity variation during spacecraft orbit control and braking.
Design features:
- A four-chamber engine based on four the 11D428A-24 thrusters with integrated propellant supply system. The thrusters are rigidly bracket-mounted.
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