The Power Distribution Unit (PDU) in a satellite aims to distribute energy across all subsystems and payloads and prevent the overload of the main power bus. The design of a PDU seeks efficient functionality, achieving a balance of performance, weight and reliability, meeting the mission requirements at the lowest possible cost without risk. The complexity and power consumption of the PDU has increased in recent decades due to new design demands, such as:
- New digital devices require lower supply voltages and higher operating currents, such as FPGA and ASIC devices.
- An increasing number of supply rails with tight power supply tolerances
- Reliable protection systems according to the needs of new devices.
- Systems to improve energy efficiency, such as sophisticated battery management and advanced power control.
- Control the primary and redundant unit of the PDU.
To prevent overloads and load short circuits failures, a PDU needs many supervisory current monitoring circuits to ensure a controlled and reliable load connection and disconnection from the main satellite bus in a failure case. For this proposal Latching Current Limiters (LCLs) circuits as an effective way.
The use of LCLs in the power system of ESA (European Space Agency) satellites have been consolidated in the last decades, this has allowed for a global European agreement on the definition of the relevant interface, which is reflected in the ECSS-E-ST-20-20C standard and the ECSS-E-HB-20-20A handbook.
Continue reading about power distribution
The LCL is a
“switchable and latching protection placed between a power source and the relevant load, causing a trip-off after having achieved at its output an overcurrent limitation for a definite trip-off time”.
The general architecture of LCL and essential elements are shown below:
- Under-Voltage Protection section
- Trip-OFF timer section
- The switch, the driver and the current sensor section
- Memory cell and switch supply section
- The auxiliary supply section
- The telemetry section
In the event of an overload, the current sensor detects if the measured value exceeds the set thresholds, causing the LCL to limit the current and activate a timer. If the overload lasts longer than a specified time (called trip-off time), the timer orders the LCL to shut down.
The LCL can be controlled ON and OFF states and with memory cell latch its last status. Generally, for the failure cases, there be an external command activation to reset the LCL into its original ON state.
Proper operation of an LCL implies (in addition to its components operating within SOA) having a correct overload limit threshold and trip-off time setting. This configuration depends on the needs of the payloads or subsystem requirements.
The current limit value of the current sensor is set by choosing properly de sense resistor value, taking into account the power dissipated in the resistance and the accuracy of the current measurement.
The voltage drop across the sensor resistor (VRSENSE) is continuously compared with the input offset (VOFFSET) of the measurement circuit, to activate the current limiter when
There are different configurations and alternatives regarding LCLs connections in the PDU, depending on the complexity of the unit power system, which is explained in ECSS-E-HB-20-20A.
References:
- ECSS-E-ST-20-20C
- ECSS-E-HB-20-20A
- Accurate current sensing in spacecraft
- Power Distribution Unit -ESA-
