Key highlights

The 6U Deployable Solar Array is a CubeSat deployable solar panel engineered to raise the orbit-average power of 6U nanosatellite missions. Each configuration carries 32 triple-junction photovoltaic cells with cell efficiency above 30% at beginning of life and above 29% at end of life, producing a peak power of up to 38.4 W in LEO for the single-deployable and X/Y double-deployable layouts (29.3 W for the Z double-deployable). A burn-wire release mechanism actuates deployment, and four ordering variants – single or double wings on Z or X/Y hinges – let mission designers match stowage volume, deployment geometry, and satellite solar power output to their bus.

Built for a five-year mission lifetime, the array operates from a single 5 V supply and protects its strings with internal bypass diodes. Up to three integrated photodiodes provide coarse sun sensing, while an accessible remove-before-flight (RBF) inhibition mechanism keeps ground handling safe and simple. Arrays can be wired in parallel to scale power generation, and optional additions – an external magnetorquer connector, a low-power MCU, extra photodiodes, and a temperature sensor – adapt the panel to each spacecraft's ADCS and power architecture. Every unit ships space-qualified with a complete user manual and direct compatibility with EnduroSat's avionics ecosystem.

Applications

Primary power generation for 6U CubeSat missions in LEO
Earth observation and remote sensing nanosatellites needing deployable solar arrays
Communications and IoT constellation spacecraft with demanding power budgets
Missions trading stowed volume against power via single or double deployable wings
Scalable satellite solar power systems using parallel-connected arrays

Key features

High-efficiency triple-junction cells:
32 space-grade photovoltaic cells with 30+% efficiency at BOL and 29+% at EOL.
Up to 38.4 W peak power in LEO:
38.4 W for Single Deployables and the X/Y Double Deployable; 29.3 W for the Z Double Deployable; up to 19.2 W per side.
Four configuration variants:
Single or Double Deployable wings with Z or X/Y hinge mounting.
Burn-wire release mechanism:
Reliable deployment actuation for the hinged panels.
Single 5 V operation:
Only one 5 V power supply is required for operation.
Reverse bias protection:
Internal bypass diodes safeguard the cell strings.
Integrated sun sensing:
Up to 3 photodiodes plus an accessible RBF inhibition mechanism.
Scalable power:
Supports parallel array connections for custom power needs.
Configurable options:
Connector for external magnetorquer, low-power MCU, up to 2 extra photodiodes, and a temperature sensor.
Five-year design life:
Designed for a 5-year satellite mission lifetime.

Customization

Panels may be connected in parallel or in series to suit different system configurations.

Can be provided with integrated sun sensors and gyroscope.

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Last updated: 2026-06-04