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3U Satellite Bus M3P

3U nanosatellite bus M3P

NanoAvionics provides nanosatellite buses based on a modular and highly integral design which extends payload volume and saves development costs for customers.

Utilization of NanoAvionics’ satellite buses enables customers to concentrate on the most important mission goals dealing only with high-level mission implementation tasks such as payload integration and its support during the mission in orbit.

Applications of the nanosatellite bus:

  • Educational missions
  • Technology in-orbit demonstration missions
  • Scientific missions
  • Commercial constellation missions and many others
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3U nanosatellite bus M3P

NanoAvionics provides nanosatellite buses based on a modular and highly integral design which extends payload volume and saves development costs for customers.

Utilization of NanoAvionics’ satellite buses enables customers to concentrate on the most important mission goals dealing only with high-level mission implementation tasks such as payload integration and its support during the mission in orbit.

Applications of the nanosatellite bus:

  • Educational missions
  • Technology in-orbit demonstration missions
  • Scientific missions
  • Commercial constellation missions and many others
  • Bus Features:
    • 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.
  • Payload Controler:
    • 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
  • Power System:
    • 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
  • Flight Computer (Including ADCS functionality):
    • 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