Hall Effect Thruster
Hall Effect Thruster
In development
A Hall effect propulsion system developed for SmallSat and CubeSat maneuvering. Thruster hardware, cathode operation, power processing and thruster control are developed together.
- Hall effect propulsion
- Discharge power & cathode control
- Thruster operating control
Key development features
- Hall discharge architecture using electric and magnetic fields for ionization and ion acceleration.
- Dedicated discharge power conversion and electrical monitoring.
- Cathode ignition and operating control coordinated with the main discharge.
- Propellant delivery interfaces for the thruster and cathode.
- Magnetic circuit design matched to the discharge architecture.
- Controlled transitions between standby, startup, firing and shutdown.
- Operating setpoints and protective limits managed by the thruster controller.
- Telemetry for discharge behavior, supply status, temperature and controller state.
- Fault responses for abnormal loads, failed starts and interrupted commands.
- Defined mounting, thrust-axis, plume-clearance and thermal-interface requirements.
System architecture
| Element | Development scope |
|---|---|
| Thruster head | Discharge channel, anode and magnetic circuit |
| Cathode assembly | Electron supply for the discharge and plume neutralization |
| Discharge supply | Regulated conversion, current sensing, filtering and protection |
| Cathode electronics | Ignition and operating supplies matched to the selected cathode |
| Magnetic field control | Magnetic circuit and, for electromagnet configurations, coil-current control |
| Propellant interfaces | Flow delivery, valves, instrumentation and operating coordination |
| Controller | Firing state machine, telemetry, inhibits and anomaly handling |
| Spacecraft interfaces | Power, data, mounting, thermal paths and operational interlocks |
Product interfaces
| Interface | Product interface parameters |
|---|---|
| Power | Input voltage, ignition demand, discharge operating power and startup transients |
| Data | Selected CAN or serial link, command timing, status and fault telemetry |
| Thermal | Mounting temperatures, heat paths, firing duration and cooldown constraints |
| Mechanical | Thruster and cathode placement, thrust-axis alignment and access |
| Electromagnetic | Conducted emissions, magnetic interaction and spacecraft coexistence |
| Operations | Startup, operating and safe-shutdown requirements |
Packaging and operating constraints
Product development defines the mounting envelope, input power demand and thermal operating limits of the thruster and its electronics. Packaging options are assessed against the customer’s stated spacecraft constraints.
Development and verification
Discharge and cathode characterization, conversion-stage testing, control-sequence verification and propulsion test campaigns establish the operating behavior of the system. Lifetime and total-impulse claims follow their own verification evidence.
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