SmallSat PCDU – STARBUCK-Mini MCC
AAC Clyde Space
An advanced SmallSat PCDU with an integrated Mission Control Computer, combining power management and satellite OBC functions into a single unit for streamlined satellite architecture.
Technical specifications
- Design Life
- 5-7 years in LEO
- System Power
- 2.5 kW
- Primary Bus Voltage
- 22-34 V
- Solar Power Regulation
- MPPT or S3R
- Battery Charge Regulation
- CC-CV
- Idle Power Consumption Range
- 10 W Typically
- Operating Temperature
- -30°C to +60°C
- Radiation Tolerance (TiD)
- 20 kRAD (qualified >30 kRAD Si)
- Mass (5 Module Configuration)
- 3.9 kg
- Mass (15 Module Configuration)
- 11.8 kg
- Width (5 Module Configuration)
- 142 mm
- Width (15 Module Configuration)
- 361 mm
- Height
- 147 mm
- Depth
- 249 mm
- 500 W Solar Array Configuration
- 20 x 28V LCLs - 6 x 5V LCLs - 6 x 12V LCLs
- 2.5 kW Solar Array Configuration
- 100 x 28V LCLs - 1.2 kW 50V output for electric propulsion
- TRL Level
- 9
- EM Lead Time
- 6 months
- FM Lead Time
- 10 months
- Flight Status
- Flown 2024
- MCC Integration
- Mission Control Computer integrated
About
The STARBUCK-Mini MCC is an evolution of the STARBUCK-Mini PCDU that integrates a Mission Control Computer (MCC) directly into the power management unit. This combined system handles both power conditioning/distribution and on-board computing functions, reducing system complexity, mass, and volume while simplifying interfaces. The MCC element provides processing and data handling capabilities typical of an OBC, enabling a more integrated satellite architecture. The system maintains all the STARBUCK-Mini PCDU features including 2.5 kW solar input power, modular scalable architecture, MPPT or S3R solar power regulation, and radiation-tolerant components, while adding the computing layer for mission control tasks.
Documentation
Need the full ICD, test reports or a specific revision? Ask the supplier directly.
