DIOO — Li-ion Satellite Battery Pack
Li-ion battery packs engineered for low-Earth orbit spacecraft — available in three standard configurations or fully customised to your mission voltage and capacity requirements. ESA BIC grant awarded April 2026 — project start July 2026.
Purpose-built for orbit
Commercial off-the-shelf battery solutions are not designed for the radiation environment, vacuum conditions, and thermal extremes of low-Earth orbit. DIOO is a proprietary battery management system built from the ground up for spacecraft applications — combining space-qualified cell selection, radiation-tolerant BMS electronics, and thermal control strategies developed specifically for LEO missions.
BMS electronics designed to operate reliably through the radiation environment of low-Earth orbit, including South Atlantic Anomaly passages.
Passive thermal design handles the extreme hot/cold cycling of LEO orbit — from direct sun exposure to eclipse shadow with each 90-minute pass.
Redundant protection circuits, cell-level monitoring, and fault isolation to meet spacecraft safety requirements and range safety standards.
Three standard variants — fully customisable
All configurations use high-grade LG MJ1 18650 Li-ion cells with a space-qualified BMS. Each variant can be adapted to any voltage and capacity requirement — contact us to discuss your mission's specific power budget.
DIOO x5
12.6 V · 524 Wh
The compact single-string configuration. Ideal for small satellites and CubeSat buses requiring a low-voltage bus with moderate energy storage.
- ✓ 12.6 V nominal bus voltage
- ✓ 524 Wh usable capacity
- ✓ Space-grade BMS with cell monitoring
- ✓ Passive thermal control design
- — Full specs at project milestone
DIOO x10
25.2 V · 1058 Wh
The primary reference design — dual-string for the common 24V satellite bus. Covers a full LEO eclipse sequence with margin for most mission profiles.
- ✓ 25.2 V nominal bus voltage
- ✓ 1058 Wh usable capacity
- ✓ Redundant BMS protection layers
- ✓ Designed for 90-min LEO eclipse cycle
- — Full specs at project milestone
DIOO x28
33.6 V · 2.8 kWh
Maximum energy for high-power missions — imaging satellites, propulsion systems, and platforms with demanding continuous power requirements throughout eclipse.
- ◎ 33.6 V nominal bus voltage
- ◎ 2.8 kWh usable capacity
- ◎ High-current discharge capability
- ◎ Fault-tolerant multi-string architecture
- — Full specs at project milestone
Need a different voltage or capacity?
The DIOO platform is designed to scale. Whether your mission needs a different bus voltage, higher capacity, specific form factor, or a particular discharge profile — we can size the pack to your requirements. Reach out with your power budget and we'll discuss what's feasible.
Purpose-sized for CubeSat platforms
A dedicated family of DIOO battery packs for CubeSat platforms — all sharing the 12.6 V EPS bus standard, built around LG MJ0 18650 cells with a space-grade BMS. Choose by power class, not just U-size: a 3U satellite with a demanding payload may need CS-M, while a low-power 6U can run fine on CS-1.
U-size ranges below are indicative. Pick the pack whose average-power range covers your mission's power budget.
DIOO CS-1
12.6 V · 44 Wh
3S1P · 3 × LG MJ0 18650
"Ideal for small CubeSats and low-power tech demos."
Typically suited to 1U–3U platforms at 1–8 W average. Covers a full eclipse with margin for beacons, simple imagers, and low-duty payloads — the right starting point for technology demonstrators and educational missions.
- ✓ 1–8 W average power class
- ✓ Typical platforms: 1U – 3U
- ✓ Full eclipse at low-duty loads
- ✓ 12.6 V CubeSat EPS bus
- — Mechanical drawings at TRL 4
DIOO CS-M
12.6 V · 176 Wh
3S4P · 12 × LG MJ0 18650
"Balanced capacity for most 3U–6U missions and many 8U platforms."
The go-to pack for 3U–8U platforms at 5–25 W average. Handles frequent downlinks, ADCS reaction wheels, and active payloads through a full eclipse sequence — the most versatile option in the CS family.
- ✓ 5–25 W average power class
- ✓ Typical platforms: 3U – 8U
- ✓ Active payloads & frequent downlinks
- ✓ Cell-level monitoring & balancing
- — Mechanical drawings at TRL 4
DIOO CS-L
12.6 V · 353 Wh
3S8P · 24 × LG MJ0 18650
"For power-hungry payloads and long eclipse operations."
Covers 6U–16U platforms at 15–50 W average. High-rate communications, high-resolution imaging, electric propulsion priming, and multi-experiment platforms — fully supported through extended eclipse with end-of-life margin.
- ◎ 15–50 W average power class
- ◎ Typical platforms: 6U – 16U
- ◎ High-duty & long eclipse operations
- ◎ Fault-tolerant multi-string BMS
- — Mechanical drawings at TRL 4
Sizing note: Eclipse energy figures assume a 93-minute LEO orbit at 550 km with a 35-minute eclipse and a depth-of-discharge not exceeding 80% to protect cell longevity over a ≥2-year mission life. U-size ranges overlap intentionally — a power-hungry 3U may need CS-M, while a low-power 8U could run on CS-1. All CS variants share the same 12.6 V bus and BMS architecture and can be customised to your EPS connector standard.
TRL & IRL Status
Invention begins. Practical applications can be envisioned.
Integration opportunity between technologies identified.
Project Milestones
- ESA BIC Slovakia grant awarded Apr 2026Done
- Project kick-off Jul 2026
- Li-ion (LG MJ1) cell selection & characterisation Q3 2026
- BMS prototype v1 — bench validation (TRL 3) Q4 2026
- Thermal-vacuum chamber testing (TRL 4) Q2 2027
- Engineering model integration Q3 2027
- Flight model qualification (TRL 6) 2028
Why space batteries matter
The Problem
- — COTS batteries fail in vacuum & radiation
- — Legacy space batteries are expensive & over-engineered
- — New-space missions lack affordable qualified options
- — LEO thermal cycling degrades unoptimised cells quickly
DIOO's Answer
- ◎ Designed for LEO from day one — not a retrofit
- ◎ Cost-competitive with new-space budget constraints
- ◎ ESA-guided development through BIC programme
- ◎ TRL-driven roadmap to flight-qualified hardware