SmallSat PCDU – STARBUCK-MINI
AAC Clyde Space
The STARBUCK-MINI is a SmallSat Power Conditioning and Distribution Unit (PCDU) designed for high-performance power control across various missions. Upgraded to deliver 2.5 kW of solar input power (67% increase from previous 1.5 kW versions), it enables higher-power payloads and extended mission flexibility. The modular, scalable architecture allows configuration with up to 15 modules for […]
Key figurescomparable across the catalogue
- Mass
- 3.9 kg
- Power
- 10 W
- Design life
- 7 years
- Lead time
- 10 months
- TRL
- 9
Normalised to common units so this product can be compared with others in its category. The supplier's own wording is below.
As published by the supplier
- 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 28 V LCLs - 6 x 5 V LCLs - 6 x 12 V LCLs
- 2.5 kw solar array configuration
- 100 x 28 V LCLs - 1.2 kW 50 V output for electric propulsion
- TRL level
- 9
- Em lead time
- 6 months
- Fm lead time
- 10 months
- Flight status
- Flown 2024
About
The STARBUCK-MINI is a SmallSat Power Conditioning and Distribution Unit (PCDU) designed for high-performance power control across various missions. Upgraded to deliver 2.5 kW of solar input power (67% increase from previous 1.5 kW versions), it enables higher-power payloads and extended mission flexibility. The modular, scalable architecture allows configuration with up to 15 modules for tailored performance. Features include COTS components combined with radiation-hardened parts, current-limiting circuits on all outputs, redundant power paths for critical payloads, internal redundancies, and single-point failure tolerance. Combines advanced power management with Maximum Power Point Tracking or S3R battery charge regulation. Used on missions including Intuitive Machines 2024 Lunar Mission, Sweden’s MATS satellite, ESA’s Arctic Weather Satellite, and Astroscale’s ELSA-M space debris removal service.
Documentation
No public datasheet yet — request the datasheet / ICD from the supplier.