High power, high reliability
satellite electronic systems.

High-power true Maximum Power Point Tracker (MPPT) with digital control. Designed to support high-current silicon cells for the most demanding high-power missions, with 1.5 kW per module. Resilience built-in with a redundant DET (Direct Energy Transfer) bypass path and dual-redundant ideal diodes. Full telemetry — all voltages, currents, and temperatures available over dual-redundant digital TMTC networks.

Regulated and unregulated load channels from a single module. Up to 12 regulated outputs across configurable rails — 3.3, 5, 12, 28, or 50 V — each protected by a latching current limiter. Trip current, current-limit time, retry behaviour, and retry period are all digitally programmable per channel; configuration supports compliance with ECSS-E-ST-20-20C. Dedicated drivers for heater loads and Hold-Down Release Mechanisms (single-LCL or two-barrier arm/fire).

External command and telemetry interface to the spacecraft. CAN is the primary host bus; RS-422 / RS-485 is available for differential serial or legacy protocols. Both are exposed as fully redundant A/B channels so a single-point failure cannot silence the PCDU. Internally, modules talk to one another over a redundant digital bus with deterministic messaging — control loops, telemetry, and protection share a common timing reference. TM/TC covers LCL configuration, secondary-converter setpoints, telemetry streaming for battery / SARs / modules / temperatures, and event and fault logging.

Drive, protection, and sensing for cold-gas, monopropellant, and electrothermal propulsion. Hit & Hold and latching solenoid valves are driven through GaN-FET H-bridges with closed-loop current control; tank heaters, nominal and redundant thruster heaters, pressure sensors, Type-K thermocouples, and NTC thermistors all share the same channel architecture. Every output is gated by a digitally configurable LCL — trip currents, hit/hold timing, and drive parameters are programmable per channel. Control runs on an FPGA hosted on a pluggable Mezzanine Board; the spacecraft DPU issues telecommands over SPI and reads back telemetry on the same link. Algorithms live on the DPU — the PDE actuates.

Drive electronics for spacecraft mechanism and propulsion-actuator motors. Two-phase stepper drive with per-winding PI current control. Resolver feedback closes the position loop; a mass-flow sensor input closes the outer loop for propellant control. Four selectable schemes — open- and closed-loop position, each available standalone or layered under a mass-flow controller — run on the same hardware for characterisation, pointing, and propellant metering.