• Empty bus mass: 1530 g
• Max payload mass: 3000 g
• Payload volume: up to 2U
• M3P bus is already pre-integrated (mechanically, electrically and functionally tested) and pre-qualified to be straight ready for the payload integration. Therefore, final flight acceptance and flight readiness procedures are minimized for the customer.
• Sample mission code is pre-installed for the customer to be able to run system diagnostics upon delivery of the bus and quick payload integration.
• Sophisticated mission code can be prepared by NanoAvionics team according to separately agreed terms and conditions.
• Payload integration service can be performed by NanoAvionics team according to separately agreed terms and conditions.
• EPSS Propulsion system as an option.

• Cortex™ M7 core, Clock speed up to 400 MHz (configurable)
• 1 MB of internal RAM
• 2 MB of internal FLASH memory
• 512 kB of FMC-connected FRAM memory
• 4 MB FMC-connected SRAM
• 256 MB of external NOR-FLASH for data storage (2 x two die (64 MB each) chips, QSPI)
• 2×512 kB of FRAM (SPI) for frequently changing data storage
• Integrated TRC
• microSD NAND Memory support (up to 2 x 32 GB)
• Three On-Board PWM Controlled H-Bridges
• PWM Outputs
• FreeRTOS
• In-Orbit firmware update
• Firmware Power-on-check and Restore
• RFS – Redundant Record-based File System
• A number of Payload dedicated interfaces:
  • 100BASE-TX Ethernet port
  • CAN Interface
  • 2 x RS422 (on request interchangeable with 2 x RS485)
  • 3 x buffered SPI
  • 2 x USART/UART
  • 2 x I2C
• CSP Support
• Self-Diagnostics
• Dynamic CPU Frequency Control
• User-friendly Console

• Input, output converter efficiency: > 96 %
• Battery cells balancing
• Configurable thermal control system
• Supported data interfaces: CAN, with CSP protocol support, UART
• Fail-safe design: in case of total microcontroller malfunction EPS will go to emergency mode and selected emergency channels will keep satellite operational

Outputs (Over-current protected):

• 4 regulated voltage rails: 3.3 V; 5 V; (3 V – 18V configurable)
• Up to 18 regulated configurable – 3.3 V / 5 V / 3V – 18 V
• Unregulated with switch: battery voltage 6.0 V – 8.4 V
• Typical output channel current: 3.13 A (configurable)
• Consistent 3.3 V Output converter power: 20 W
• Consistent 5 V Output converter power: 20 W
• Consistent 3-18 V Output converter power: 20 W
• Min unregulated output power with on-board battery back (2S1P configuration): 25 W
• Min unregulated output power with external battery pack (2S7P configuration): 175 W

Inputs:

• 4 MPPT converters (8 channels) with integrated ideal blocking diodes
• Voltage: 2.6 – 18 V
• Max charging power with on-board battery back (2S1P configuration): 10 W 
• Max charging power with extended battery pack (2S7P configuration): 70 W 

Batteries:

• Standard battery (EPSL): 2 cells, 7.4 V, 3200 mAh, 23 Wh
• Optional extended battery pack (EPSH): 4 cells, 7.4 V, 6400 mAh, 46 Wh

• ARM 32-bit Cortex™ M7 CPU with clock speed up to 400 MHz (configurable)
• FreeRTOS
• In-orbit firmware update and Self-Diagnostics
• CSP, KISS support
• Mission planner with time scheduled script/task execution support
• Telemetry logging

ADCS sensors and actuators:

• NanoAvionics Sun Sensors
• Integrated magnetic and inertial sensors
• Reaction Wheels System NanoAvionics “SatBus 4RW0”
• Integrated NanoAvionics Magnetorquers

Attitude control type: 3-axis stabilization

Eventual Attitude determination and Control System accuracy

(including mechanical displacements of the physical body of

the satellite): up to 0.1° of pointing; 0.05° of knowledge in default

configuration

Stability accuracy (Jitter): ± 0.015°/s (at f = 4 Hz)

Attitude maneuver ability (Slew rate): 3-10°/s

Operational modes:

• Sun pointing mode
• Nadir pointing mode
• Velocity pointing mode
• Ground geodetic coordinate pointing mode
• Client defined pointing mode