Microsatellite Bus Platform
Modular, radiation-hardened satellite bus architecture designed for 10–100 kg class missions. Fully configurable power, ADCS, comms, and propulsion subsystems for LEO, MEO, and cislunar operations.
Modular Architecture
Standardized form factors with plug-and-play payload interfaces. Rapid integration via 1553B, CAN, or SpaceWire data buses with unified ground software stack.
Advanced ADCS
3-axis stabilized with ±0.05° pointing accuracy. Redundant star trackers, IMUs, and reaction wheel assemblies enable high-resolution Earth observation and precision formation flying.
Propulsion Options
Select from cold-gas thrusters, resisto-jet, or electric propulsion (Hall/Xenon). Supports orbit insertion, station-keeping, de-orbit, and constellation deployment maneuvers.
Radiation Hardening
Flight-proven COTS and RHBD components. Survives TID up to 30 krad(Si) and SEE environments typical of polar, GEO transfer, and cislunar trajectories.
Technical Specifications
| Bus Dry Mass | 6.2 kg – 28.5 kg (model dependent) |
| Payload Capacity | 2.5 kg – 35 kg |
| Bus Dimensions | 450×450×600 mm (standard chassis) |
| Power Generation | 45W – 250W EOL (GaAs triple-junction arrays) |
| Energy Storage | Lithium-ion or Lithium-polymer (1000+ cycles) |
| Attitude Control | 3-axis, magnetic torquers + RWAs / CMGs |
| Pointing Accuracy | ±0.05° (boresight), ±0.1° (3σ) |
| Command & Telemetry | S-band (TTC), X/Ka-band (payload) |
| Data Handling | Up to 500 Mbps internal bus, 4 TB solid-state recorder |
| Thermal Management | Passive coatings, louvers, conductive straps, heaters |
| Launch Compatibility | SpaceX, Rocket Lab, ISRO, Arianespace, Virgin Orbit |
| Mission Life | 3 – 7 years (orbit/environment dependent) |
Platform Configurations
MVB-10
10 kg Class- Bus Mass6.2 kg
- Power (EOL)45 W
- Payload Interface1553B / CAN
- OrbitLEO (300-800 km)
MVB-25
25 kg Class- Bus Mass14.8 kg
- Power (EOL)120 W
- Payload InterfaceSpaceWire / 1553B
- OrbitLEO / MEO Transfer
MVB-50
50 kg Class- Bus Mass28.5 kg
- Power (EOL)250 W
- Payload InterfaceSpaceWire / MIL-STD-1760
- OrbitLEO / Cislunar / GEO Transfer
Engineering Documentation
Technical Datasheet v4.2
PDF • 2.4 MB
CAD & Mechanical Drawings
STEP / DXF • 15 MB
Electrical Interface Control
PDF • 4.1 MB
Qualification Test Reports
PDF • 8.7 MB
Ready to Integrate Your Payload?
Our systems engineering team will provide a tailored configuration review, mass/power budget analysis, and delivery timeline within 5 business days.